U.S. patent application number 17/355751 was filed with the patent office on 2021-12-30 for monitoring system.
The applicant listed for this patent is Drager Safety AG & Co. KGaA. Invention is credited to Henning GERDER, Christoph OSTERLOH.
Application Number | 20210405008 17/355751 |
Document ID | / |
Family ID | 1000005724247 |
Filed Date | 2021-12-30 |
United States Patent
Application |
20210405008 |
Kind Code |
A1 |
GERDER; Henning ; et
al. |
December 30, 2021 |
MONITORING SYSTEM
Abstract
A monitoring system (100) is provided for flight crew members
(99), e.g., aviators, pilots, copilots or passengers, of airplanes
or aircraft, e.g., airplanes or helicopters of the civil or
military aviation, passenger planes in the scheduled or charter
service, especially also ultrafast passenger planes. The monitoring
system includes a sensor mechanism and a control unit configured to
organize a procedure of a measurement-based monitoring of the gas
composition of air, breathing air or breathing gases with the
sensor mechanism in an airplane or aircraft, and to control or
regulate the procedure. A measurement-based detection of gas
concentrations is carried out with the sensor mechanism (60).
Inventors: |
GERDER; Henning; (Lubeck,
DE) ; OSTERLOH; Christoph; (Lubeck, DE) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Drager Safety AG & Co. KGaA |
Lubeck |
|
DE |
|
|
Family ID: |
1000005724247 |
Appl. No.: |
17/355751 |
Filed: |
June 23, 2021 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
62705456 |
Jun 29, 2020 |
|
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|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
A62B 7/14 20130101; G01N
33/0063 20130101; G01N 33/0011 20130101; A62B 9/006 20130101 |
International
Class: |
G01N 33/00 20060101
G01N033/00; A62B 9/00 20060101 A62B009/00 |
Foreign Application Data
Date |
Code |
Application Number |
Jun 29, 2020 |
DE |
10 2020 117 040.8 |
May 4, 2021 |
DE |
10 2021 111 431.4 |
Claims
1. A monitoring system for monitoring a gas composition of air,
breathing air or breathing gases in airplanes or aircraft, the
monitoring system comprising: a sensor mechanism; and a control
unit configured to organize a procedure of a measurement-based
monitoring of the gas composition of air, breathing air or
breathing gases with the sensor mechanism in an airplane or
aircraft, and to control or regulate the procedure of the
measurement-based monitoring of the gas composition of air,
breathing air or breathing gases in the airplane or aircraft.
2. A monitoring system in accordance with claim 1, wherein the
procedure of the measurement-based monitoring comprises a
qualitative and quantitative measurement-based detection of a
concentration of oxygen with the sensor mechanism.
3. A monitoring system in accordance with claim 1, wherein the
procedure of the measurement-based monitoring comprises a
qualitative and quantitative measurement-based detection of a
concentration of carbon dioxide with the sensor mechanism.
4. A monitoring system in accordance with claim 1, wherein the
procedure of the measurement-based monitoring comprises a
qualitative and quantitative measurement-based detection of a
concentration of carbon monoxide with the sensor mechanism.
5. A monitoring system in accordance with claim 1, wherein the
sensor mechanism comprises a sensor configured as at least one of
an oxygen sensor, a carbon dioxide sensor and a carbon monoxide
sensor.
6. A monitoring system in accordance with claim 1, wherein the
control unit is configured to also take into consideration and/or
to also include in the procedure at least one environmental
parameter and/or at least one situational parameter.
7. A monitoring system in accordance with claim 1, further
comprising a data interface.
8. A monitoring system in accordance with claim 1, further
comprising a data interface receiving and/or providing
environmental parameters and/or situational parameters.
9. A monitoring system in accordance with claim 1, wherein the
sensor mechanism comprises: a sensor configured as a gas sensor;
and an additional sensor configured to determine and/or to
measurement-based detect environmental parameters and/or to
determine and/or to measurement-based detect situational parameters
and wherein the sensor mechanism is configured for providing the
environmental parameters and/or situational parameters.
10. A monitoring system in accordance with claim 1, further
comprising a gas transport module comprising a pump with a gas port
for connection with a measured gas line to deliver quantities or
partial quantities of breathing gas or breathing air from a
measuring point, via the measured gas line, to the sensor
mechanism.
11. A monitoring system in accordance with claim 10, further
comprising a gas inlet of the monitoring system, wherein the gas
transport module is arranged at the gas inlet of the monitoring
system.
12. A monitoring system in accordance with claim 10, further
comprising a gas outlet of the monitoring system, wherein the gas
transport module is arranged at the gas outlet of the monitoring
system.
13. A monitoring system in accordance with claim 10, further
comprising: an additional gas port; and a reversing valve.
14. A monitoring system in accordance with claim 13, further
comprising an additional pump arranged at the additional gas
port.
15. A monitoring system in accordance with claim 10, wherein the
control unit is configured to control the gas transport module.
16. A monitoring system in accordance with claim 15, wherein the
control unit is configured to also take into consideration and/or
to also include in the control at least one environmental parameter
and/or at least one situational parameter.
17. A monitoring system in accordance with claim 1, wherein the
control unit is configured to determine and/or detect an alarm
situation and to organize an alarm generation or alarm and/or
provide an alarm signal.
18. A monitoring system in accordance with claim 17, wherein the
control unit is configured to also take into consideration an
environmental parameter and/or a situational parameter in the
organization of the alarm generation or alarm and/or to also
include the environmental parameter and/or the situational
parameter in the organization of the alarm generation.
19. A monitoring system in accordance with claim 1, further
comprising at least one an energy storage device.
20. A monitoring system in accordance with claim 1, further
comprising at least one operating element, for operating the
monitoring system.
21. A monitoring system in accordance with claim 1, further
comprising at least one display element for displaying events,
situations, status data, current measured values, past measured
values, measured variables derived from measured values, including
maxima or minima, mean values, trends, statistics, events and alarm
situations.
22. A monitoring system in accordance with claim 1, further
comprising an input element configured to receive user input
comprising user initiates annotation, triggering, starting or
ending defined situations, defined actions or states at the
monitoring system.
23. A monitoring system in accordance with claim 22, wherein the
input element is configured as an acceleration sensor.
24. A monitoring system in accordance with claim 1, further
comprising a memory for storing measured values and measured
variables derived from the measured values including maxima or
minima, mean values, trends, statistics, events, alarm
situations.
25. A monitoring system ion accordance with claim 6, wherein the
control unit is configured to also take into consideration an
environmental parameter and/or a situational parameter during
signal processing and/or signal filtering of the measured values of
the sensor mechanism and/or to also include the environmental
parameter and/or the situational parameter in an adaptation of the
signal processing.
26. A monitoring system in accordance with claim 1, further
comprising a monitoring system memory, wherein the control unit is
configured to use predefined threshold values, which are storable
for determined values of gas concentrations in the monitoring
system memory, in the organization of the alarm generation.
27. A monitoring system in accordance with claim 1, wherein the
control unit is configured to use an early warning system for the
detection of hypoxia on a basis of current and past measured values
of the sensor mechanism by means of a decision matrix or adapted
algorithms or teachable or self-learning algorithms.
28. A monitoring system in accordance with claim 27, wherein the
control unit is configured to take into consideration physiological
data in the early warning system for the detection of hypoxia.
29. A monitoring system in accordance with claim 1, wherein an HME
filter element is arranged in the measured gas line, at the gas
inlet or at the gas transport module.
30. A monitoring system in accordance with claim 1 in combination
with a breathing gas mask connected to the sensor mechanism by a
measured gas line and further comprising: a memory; a pressure
sensor; and a shut-off valve, wherein the control unit is
configured together with a pressure sensor and the shut-off valve
and the memory to determine a current pressure level in the
breathing mask.
31. A monitoring system in accordance with claim 30, wherein the
control unit is configured to determine a static pressure level and
a dynamic pressure level; to determine an offset pressure level
based on a static pressure level and a dynamic pressure level; and
determine the current pressure level in the breathing mask taking
into consideration the dynamic pressure level by means of a
measurement maneuver.
32. A monitoring system in accordance with claim 31, wherein the
control unit is configured to take into consideration information
concerning breathing phases of an aviator user of the breathing
mask during the measurement-based detection and/or determination of
the static pressure measured value and/or of the dynamic pressure
measured value during the performance of the measurement
maneuver.
33. A process for operating a monitoring system, the process
comprising the steps of: providing a monitoring system for
monitoring a gas composition of air, breathing air or breathing
gases in airplanes or aircraft, the monitoring system comprising a
sensor mechanism and a control unit control unit configured to
organize a procedure of a measurement-based monitoring of the gas
composition of air, breathing air or breathing gases with the
sensor mechanism in an airplane or aircraft, and to control or
regulate the procedure of the measurement-based monitoring of the
gas composition of air, breathing air or breathing gases in the
airplane or aircraft; activating the sensor mechanism of the
monitoring system; preparing a data storage with initialization of
a memory of the monitoring system; carrying out a measurement-based
detection of measured values of the sensor; and storing data of the
measured values, as a data storage of the measured values of the
sensor mechanism, in the memory with corresponding time information
by the control unit.
34. A process in accordance with claim 33, wherein an additional
storage of situational parameters and/or environmental parameters
is carried out with the corresponding time information during the
data storage of the measured values of the sensor mechanism.
35. A process for operating a monitoring system in accordance with
claim 33, further comprising providing an input element configured
to receive user input comprising user initiates annotation,
triggering, starting or ending defined situations, defined actions
or states at the monitoring system, wherein an additional detection
of measured values of the sensor mechanism, which detection is
independent from a time control, is carried out in case of
activation of the input element on activation of an input element.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of priority under 35
U.S.C. .sctn. 119 of German Application 10 2020 117 040.8, filed
Jun. 29, 2020, U.S. Provisional Application 62/705,456, filed Jun.
29, 2020, and German Application 10 2021 111 431.4, filed May 4,
2021, the entire contents of which are incorporated herein by
reference.
TECHNICAL FIELD
[0002] The present invention pertains to a monitoring system for
flight crew members or passengers of airplanes or aircraft.
Airplanes or aircraft are defined as airplanes or helicopters of
the civil or military aviation, e.g., passenger planes in scheduled
or charter service as well as ultrafast airplanes close to the
range or above the range of supersonic speed. In particular,
flights with jet planes (jets) with supersonic speeds and/or at
flight altitudes above 15,000 m above sea level represent high
requirements on the flight crew members, especially on the pilots
of jet planes, concerning the fitness to fly comprising physical
and mental fitness, attention, ability to concentrate and
alertness. In order for the physical and mental fitness and the
alertness necessary for piloting the aircraft to be guaranteed at
any time at high altitudes, during terrifically fast flight
maneuvers or in flight positions, for example, curve flight, during
nosedives, inverted flying at high speeds (>Mach 1) and with
accelerations above or even several times the gravitational
acceleration as well as also in-flight refueling, secured supply of
the aviator with satisfactory breathing air that is harmless for
health is also very essential in addition to a reliable equipment
of the airplane. For example, systems which use--usually processed
or air-conditioned and filtered--outside air from the environment
as the source of the breathing gas, are used to supply aviators,
pilots, copilots or passengers with breathing air or breathing gas,
but systems in which additional oxygen is added to the breathing
air or to the breathing gas are used as well. The oxygen may be
carried along in the airplane here, for example, under high
pressure (<200 bar) in compressed oxygen cylinders and its
pressure can be reduced to a pressure suitable for breathing by
means of suitable pressure-reducing devices or it may be generated
for the consumption during the mission by a chemical oxygen
generator, for example, from sodium chlorate, which is carried
along, in a chemical process. It is often made possible for the
aviator, pilot or copilot to activate the dispensing or supply of
oxygen independently and/or to set or preset the quantity and/or a
concentration of oxygen and/or a composition of the breathing gas
independently. The breathing air/breathing gas supply may be
ensured in this case directly from the air of the cabin or cockpit,
but it is also possible to use a tube system with mouth/nose mask
for the direct feed and/or removal of breathing air/breathing gas
to the aviator, pilot or copilot. It is necessary in each case for
the on-board equipment of the airplane or aircraft to supply the
aviator, pilot or copilot during the mission with satisfactory
breathing gas that is harmless for the health. This includes, on
the one hand, that the qualitative and quantitative composition of
the breathing gas, especially the percentages of oxygen and/or
carbon dioxide, in the breathing gas be in a range that is harmless
for health. In addition to such components as nitrogen and noble
gases, oxygen (O.sub.2) is present in the natural atmosphere at a
percentage of 21 vol. %. The percentage of carbon dioxide
(CO.sub.2) is currently below 0.05 vol. % as a worldwide average in
the natural atmosphere. According to recommendations of the U.S.
Federal Aviation Administration (FAA), a carbon dioxide
concentration of 30,000 ppm, corresponding to 3 vol. % CO.sub.2,
represents the highest allowable value for passengers in airplanes.
The American Society of Heating, Refrigerating and Air-Conditioning
Engineers (ASHRAE) recommends as the upper limit a carbon dioxide
concentration of 1,000 ppm, corresponding to 0.1 vol. % of
CO.sub.2. Thus, a concentration above 21 vol. % is also desirable
for the supply of breathing gas for aviators, pilots or copilots or
passengers for the percentage of oxygen and an upper limit of 0.1
vol. % of CO.sub.2 is desirable for the concentration of carbon
dioxide during the mission at least according to the
recommendations of the U.S. Federal Aviation Administration (FAA)
and according to the recommendations of the American Society of
Heating, Refrigerating and Air-Conditioning Engineers (ASHRAE). It
is considered to be scientifically ascertained that concentrations
of carbon dioxide above 1 vol. % to 3 vol. % may cause a carbon
dioxide poisoning, which is characterized, for example, by nausea,
headache and dizziness. Carbon dioxide concentrations above 12% are
immediately lethal. Supply with an insufficient quantity of oxygen
may also be harmful for health especially for aviators, pilots or
copilots, because the oxygen partial pressure in the blood may be
reduced in case of a supply with insufficient quantities of oxygen,
and a so-called hypoxic state (hypoxia) develops. Such a reduction
of the arterial oxygen partial pressure in the blood--also called
hypoxemic hypoxia (hypoxemia)--frequently develops in persons who
are at a high altitude. Symptoms of hypoxia are, for example,
anxiety and restlessness, dyspnea, cyanosis, tachycardia, an
increase in blood pressure, confusion, dizziness, bradycardia and
even cardiac arrest.
TECHNICAL BACKGROUND
[0003] A device and a process for monitoring inhaled gas is known
from EP 3287173 A1. A pressure level of the entire inhaled
breathing air and an oxygen partial pressure in the inhaled
breathing air are determined during the admission of the breathing
air into a face mask of a person and a partial pressure of the
oxygen in the lungs of the person is estimated from this. A
breathing mask with display device, which is configured to provide
data and/or information for aviators, pilots or copilots in a
visual form, is known from US 2007181129 A1. The display device is
configured as a so-called head-up display. The data and/or
information are projected here on the inside onto the visor into
the field of view of the aviator, pilot or copilot. Another head-up
display is known from U.S. Pat. No. 7,391,574 B2. A face mask with
a detection device for ambient temperature and the display and
visualization thereof are known from US 2016253561 A. A display
device for a face mask in a configuration as a so-called in-mask
display is known from US 2019118008 A1. A device for oxygen supply
for an airplane, for example, according to the principle of the
pressure swing adsorption, is known from U.S. Pat. No. 8,210,175
B2. Oxygen is provided, in addition, from an oxygen reserve. The
air is processed with molecular sieve beds, which are scavenged
with oxygen from the oxygen reserve at the beginning of the
operation. Other devices for oxygen supply in airplanes are known
from U.S. Pat. No. 7,407,528 B2, US 2004245390 A1 and U.S. Pat. No.
7,264,647 B2. A compressed air monitoring system for monitoring
compressed air with a measuring air line for the continuous
sampling of compressed air from a compressed air supply line and
with at least one sensor for the continuous detection of at least
one parameter of the compressed air is known from DE 102010014222
B4. A sensor for detecting a concentration of carbon dioxide, a
sensor for detecting a concentration of nitrogen dioxide, a sensor
for detecting a concentration of sulfur dioxide, a sensor for
detecting a concentration of oxygen as well as a sensor for
detecting a relative humidity of the air in the measured air line
are mentioned as sensors for the continuous detection of at least
one parameter of the compressed air. EP 2148616 B1 shows a
measuring system with a plurality of sensor mechanisms, such as
flow sensor mechanism, temperature sensor mechanism, pressure
sensor mechanism, humidity sensor mechanism, gas sensor mechanism
for the measurement of oxygen, carbon dioxide, carbon monoxide,
nitrogen, nitrogen oxides, anesthetic gases, gaseous components in
the exhalation as well as other gases. DE 102006030242 A1 shows a
configurable measuring system with a plurality of gas sensors.
Electrochemical, infrared optical and catalytic gas sensors may be
configured as gas sensors in the measuring system. A pump for
delivering quantities of air is known from US 20130167843 A1. The
pump has a piezoelectric manner of functioning. Such a pump is
suitable for delivering quantities of gas from a measuring point to
a location of the sensor mechanism and/or for measurement-based
detection by means of the measured gas line (sample line) and is
suitable, for example, for use for a side stream measurement (side
stream) for an analysis of gas components, especially also carbon
dioxide and oxygen, close to the mouth/nose area of a person or
patient for the analysis of inhaled/exhaled air. Many different
embodiments and configurations of and with gas delivery devices,
pumps or devices for transporting gas for supplying persons with
breathing gases, also in embodiments and with suitability for
ventilating persons, are known from the patent documents WO
2018033224 A1, US 20180163712 A1, WO 2018033225 A1, US 20180133420
A1, US 20180110957 A1, WO 2019072606 A1, DE 102017009605 A1, DE
102017009606 A1, DE 102018004341 A1 and also DE 202012013442 U1.
Other embodiments of gas delivery devices, pumps or devices for
transporting gas for supplying persons are known from the German
patent applications 102019003643.3, 102019003607.7, 102019004450.9
and 102019004451.7, which have not yet been laid open to public
inspection. Many different embodiments and configurations of gas
delivery devices, pumps or devices for transporting gas for feeding
gases to be measured to a gas measuring device are known from the
patent documents DE 102016013756 A1, US 20180143171 A1, US
20180143170 A1 and US 201803354 A1. A connection element, a
so-called Y-piece, for connecting ventilation tubes at the
mouth/nose area of a person or of a patient with sensor mechanism
components, components for measured value acquisition, signal
processing, signal analysis and display is known from US 2008264418
A1. The sensor mechanism components comprise a breath flow sensor
mechanism with pressure sensor mechanism, a sensor mechanism for
measuring the oxygen partial pressure, temperature sensor
mechanism, flow rate sensor mechanism, configured as a hot wire
anemometer or ultrasonic flow sensor, as well as connection
elements for EKG and blood pressure measurement. Oxygen sensors
according to the principle of measurement of the so-called
luminescence quenching, which may be arranged in the side stream in
or at the breathing gas path of a patient, are known from U.S. Pat.
No. 7,897,109 B2, U.S. Pat. No. 7,335,164 B2, U.S. Pat. No.
6,616,896 B2, U.S. Pat. Nos. 5,789,660 A and 6,312,389 B1. An
oxygen sensor with a bioreactor array is known from DE 102010037923
B4. A system for detecting a reduced oxygen supply in pilots and
for reducing the reduction of the oxygen supply in pilots is known
from U.S. Pat. No. 9,867,563 B2. A galvanic cell for measuring
oxygen is known from US 2003194351 A1. Electrochemical oxygen
sensors are known from DE 102004062052 B4 and DE 19726453 C2. An
electrochemical sensor for measuring gaseous components in a gas
mixture is known from DE 2155935. Many different embodiments of
electrochemical gas sensors, which are suitable for a
measurement-based detection of oxygen or other gases, are known
from U.S. Pat. No. 5,958,200 A, DE 102009010773 B4, DE 102005026491
B4, DE 102005026306 B4 and U.S. Pat. No. 8,496,795 B2. DE
102005007539 A1 shows an electrochemical gas sensor for a
quantitative determination of redox-active substances in very low
concentration ranges. The electrochemical principle of measurement
is suitable, depending on the configuration of the electrodes and
of the electrolyte, for the detection of different gases, for
example, oxygen, ammonia, sulfur dioxide, hydrogen peroxide,
hydrogen sulfide, nitrogen dioxide, nitrogen monoxide, arsine,
silanes, formaldehyde, acetylene, carbon monoxide, phosgene, and
phosphine. An electrochemical carbon monoxide sensor is known from
DE 19912100 A1. An electrochemical carbon dioxide sensor is known
from U.S. Pat. No. 4,851,088 A. U.S. Pat. No. 5,473,304 A and DE
4020385 C2 show heat tone sensors manufactured according to ceramic
film technology. U.S. Pat. No. 7,875,244 B2, GB 2210980 A1 and DE
19610912 A1 show heat tone sensors of the pellistor configuration.
US 2010221148 A1 and U.S. Pat. No. 5,902,556 A show catalytic gas
sensors with semiconductor chips as measuring elements. Catalytic
gas sensors are known from U.S. Pat. No. 2,816,863 A, US 2019178827
A1, U.S. Pat. No. 8,425,846 B2, U.S. Pat. No. 9,625,406 B2, U.S.
Pat. No. 6,756,016 B2, US 2016178412 A1, and U.S. Pat. No.
6,344,174 B1. The catalytic principle of measurement, also called
heat tone principle, is especially suitable for detecting
combustible and/or explosive gases, especially hydrocarbon
compounds, as well as for the determination of residual components
of combustion processes. For example, toluene, ammonia, benzene,
propane, methane, methanol, octane, butane, ethylene can be
detected by measurement based on the heat tone principle. Catalytic
sensors are frequently used to monitor limit values, e.g., the LEL
(Lower Explosion Limit). U.S. Pat. No. 4,175,422 A shows a gas
sensor with a semiconductor element as the measuring element. A gas
sensor device with semiconductor sensor mechanism configured
according to chip technology for monitoring combustion processes in
internal combustion engines of a motor vehicle is known from U.S.
Pat. No. 9,958,305 B2. Miniaturized semiconductor gas sensors are
known from DE 102004048979 B4 and U.S. Pat. No. 4,902,138 A. A
semiconductor type carbon monoxide sensor is known from DE
102012022136 B4. Miniaturized semiconductor oxygen sensors,
configured according to the microstructured technology, so-called
MEMS (micro-electromechanical system) technology, are known from
U.S. Pat. No. 9,818,937 B2 and U.S. Pat. No. 9,234,876 B2.
Furthermore, gas sensors with solid electrolytes, e.g., on the
basis of zirconium dioxide, are known. Thus, DE 102008056279 B4
shows a device with a heated solid electrolyte oxygen sensor and
with an ultrasonic sensor for the indirect detection of the
concentration of carbon dioxide. U.S. Pat. No. 5,026,992 A shows a
gas sensor for the measurement-based optical detection of methane.
U.S. Pat. No. 8,399,839 B2 shows a gas sensor for the
measurement-based optical detection of carbon dioxide. A device
with a lambda probe for detecting a quantity of residual oxygen in
the exhaust gas of an internal combustion engine is known from EP
0149619 A1. A Hall effect oxygen sensor is known from U.S. Pat.
Nos. 4,667,157 A. 8,596,109 B2, 9,360,441 B2, 4,808,921 A,
6,430,987 B1, 6,952,947 B2, 6,895,802 B2, 6,405,578 B2, 4,683,426
A, 4,173,975 A, 3,646,803 A, 3,584,499 A, 2,944,418 A and WO
16162287 A1 show devices for measuring concentrations of
paramagnetic gases. Especially a qualitative and also quantitative
measurement-based detection of oxygen is possible with such
devices, because oxygen possesses paramagnetic properties. A
measuring element for a paramagnetic gas sensor, especially for an
oxygen sensor, is known from U.S. Pat. No. 9,360,441 B2. The
paramagnetic gas sensor or oxygen sensor may preferably be arranged
in the side stream in or at the breathing gas path of a patient.
Gas-measuring devices are described in DE 102010047159 B4 and in US
2004238746 A1. An infrared optical gas-measuring device is
described in U.S. Pat. No. 5,739,535 A. An infrared optical carbon
dioxide sensor, a so-called IR carbon dioxide sensor, is known from
U.S. Pat. No. 8,399,839 B2. Devices for the measurement of the
concentration of carbon dioxide in breathing gas by measuring the
thermal conductivity are known from DE 102010047159 B4 and U.S.
Pat. No. 6,895,802 B2. The configuration according to DE
102010047159 B4 shows a carbon dioxide sensor with a semiconductor
chip as a measuring element for detecting changes in thermal
conductivity. Infrared optical carbon dioxide sensors are known
from U.S. Pat. No. 5,696,379 A, US 2004203169 A1 and U.S. Pat. No.
4,050,823 A. Infrared optical carbon dioxide sensors, which may be
arranged in the main stream in the breathing gas path of a patient,
are known from U.S. Pat. No. 8,448,642 B2, U.S. Pat. Nos. 5,095,900
A, 5,067,492 A, WO 20109115 A1, US 2019105457 A1, U.S. Pat. No.
6,095,986 A, USD 727492 S and U.S. Pat. No. 5,942,755 A.
Gas-measuring devices or sensors for the measurement-based
detection of carbon dioxide, especially also suitable for the
measurement-based detection of carbon dioxide in breathing gases,
are known from US 2002036266 A1, US 2004238746 A1, US 20180120224
A1 and US 20180116555 A1. Other gas-measuring devices or sensors
for the measurement-based detection of carbon dioxide are known
from the German patent applications 102020114972.7 and
102020114968.9, which have not yet been laid open to public
inspection. A combined sensor comprising an infrared optical carbon
dioxide sensor with a flow sensor, which may be arranged in the
main stream in the breathing gas path of a patient, is known from
U.S. Pat. No. 6,571,622 B2. Infrared optical carbon dioxide
sensors, which may be arranged in the side stream in or at the
breathing gas path of a patient, are known from US 2004238746 A1
and US 2002036266 A1. U.S. Pat. No. 6,954,702 B2, U.S. Pat. No.
7,606,668 B2, U.S. Pat. No. 8,080,798 B2, U.S. Pat. No. 7,501,630
B2, U.S. Pat. No. 7,684,931 B2, U.S. Pat. No. 7,432,508 B2, and
U.S. Pat. No. 7,183,552 B2 show gas-measuring systems for detecting
gas concentrations in the side stream and in the main stream.
Interferometers configured as gas measuring devices are described
in U.S. Pat. No. 9,939,374 B2 and U.S. Pat. No. 7,705,991 B2.
Laser-based devices for detecting gas components are known from
U.S. Pat. No. 6,274,879 B1 and EP 2788739 B1. A gas sensor
configured as a photoionization detector is known from U.S. Pat.
No. 9,459,235 B2. Other aspects concerning a qualitative and
quantitative composition of the breathing gas pertain to the
requirement that the breathing gas should be largely free from
impurities, for example, it should be largely free from foreign
bodies or particles, e.g., soot, dust, pollen or vapors of
materials, through which the breathing gas flows on its way to
aviators, pilots, copilots and passengers. Furthermore, no or no
substantial quantities of gases or gas mixtures that are harmful to
health, such as carbon monoxide (CO), ozone, traces of other gases
or traces of aviation fuel or kerosene, quantities of exhaust gases
or residues of the combustion or other air-borne pollutants shall
be present in the breathing gas. These include, for example, many
different compositions of hydrocarbons, benzenes, nitrogen oxides
(NO.sub.2, NO.sub.x), sulfur oxides (SO.sub.2, SO.sub.x), dioxins,
furanes, particles, e.g., soot, fine dust, and ultrafine particles.
In particular, carbon monoxide poisoning shall also be pointed out,
in particular, in this connection in addition to the
above-mentioned carbon dioxide poisoning. Even concentrations above
200 ppm (0.02%) cause headache and a loss of judgement, and
concentrations above 800 ppm (0.08%) cause dizziness, restlessness,
nausea, anxiety and spasms within 45 minutes and loss of
consciousness within 2 hours, possibly leading to death. The oxygen
transportation capacity of the blood decreases in case of carbon
monoxide poisoning due to a reduction of the hemoglobin level
(anemia) or due to impairment of the oxygen-binding capacity in the
blood, and anemic hypoxia develops.
SUMMARY
[0004] Therefore, the need arises to ensure the situation for
aviators, pilots, copilots, and passengers that satisfactory and
high-quality breathing gas is provided by the on-board equipment of
an airplane or aircraft during the flying operation and it can be
administered to aviators, pilots, copilots and passengers of
airplanes or aircraft. From this arises as an object of the present
invention the need to provide a monitoring system for aviators,
pilots, copilots and passengers of airplanes or aircraft or to
provide a process, which makes it possible to monitor breathing
gases and breathing air on the basis of measurements in airplanes
or aircraft. From this arises as another object of the present
invention the need to provide a process for the measurement-based
monitoring of breathing gases and breathing air in airplanes or
aircraft.
[0005] The object is accomplished, in particular, by a monitoring
system for monitoring a gas composition of breathing gases in
airplanes or aircraft with the features according to the
invention.
[0006] The object is also accomplished by a process for operating a
monitoring system for monitoring a gas composition of breathing
gases in airplanes or aircraft with the features of according to
the invention. Further features and details of the present
invention and advantageous embodiments appear from the description
and from the drawings. References used here refer to the further
configuration of the subject of the principal claim by the features
of the respective subclaim and they shall not be considered to
represent abandonment of the wish to achieve an independent
concrete protection for the combinations of features of the
referred-back subclaims. Furthermore, it shall be assumed in
respect to an interpretation of the claims as well as of the
description in case of a more specific concretization of a feature
in a dependent claim that such a limitation is not present in the
respective preceding claims as well as in a more general embodiment
of the concrete system or process. Any reference in the description
to aspects of dependent claims shall accordingly also expressly
imply a description of optional features even without a special
reference. Finally, it shall be noted that the monitoring system
being proposed here may also be varied corresponding to the process
claims and vice versa, for example, by the monitoring system
comprising devices that are intended and/or set up for carrying out
one or more process steps or by the process comprising steps that
can be carried out by means of the monitoring system or are
suitable for operating the monitoring system. Features and details
that are described in connection with the monitoring system being
proposed for flight crew members or passengers of airplanes or
aircraft and of possible embodiments are thus, of course, also
valid in connection with and in respect to a process carried out
during the operation of the monitoring system and vice versa, so
that reference is and can always mutually be made to the individual
aspects of the present invention concerning the disclosure.
[0007] Embodiments create possibilities for a measurement-based
monitoring of the gas composition of air, breathing air or
breathing gases in airplanes or aircraft. At least some exemplary
embodiments of the present invention pertain to a monitoring system
for monitoring the gas composition of air, breathing air or
breathing gases in airplanes or aircraft. At least some exemplary
embodiments of the present invention pertain to a monitoring system
for monitoring the gas composition of air, breathing air or
breathing gases in airplanes or aircraft. At least some exemplary
embodiments of the present invention pertain to a process for
operating a monitoring system for monitoring the gas composition of
air, breathing air or breathing gases in airplanes or aircraft. A
measurement-based detection of properties of at least one gas may
be made possible by means of a sensor mechanism of a monitoring
system in at least some exemplary embodiments. Properties of a gas
may include, for example, physical and other properties: Pressure,
density, viscosity, thermal conductivity, electrical and magnetic
properties, temperature, gas composition, moisture content,
toxicity, calorific value, combustibility, binding capacities with
other gases or liquids, for example, water or blood. A qualitative
measurement-based detection of at least one gas may be made
possible in at least some exemplary embodiments. A quantitative
measurement-based detection of at least one gas and/or of a
concentration of a gas may be made possible in at least some
exemplary embodiments. A qualitative and a quantitative
measurement-based detection of at least one gas may be made
possible in at least some exemplary embodiments. A qualitative and
a quantitative measurement-based detection of oxygen may be made
possible in at least some exemplary embodiments. A qualitative and
a quantitative measurement-based detection of carbon dioxide may be
made possible in at least some exemplary embodiments. A qualitative
and a quantitative measurement-based detection of another gas,
especially carbon monoxide, may be made possible in at least some
exemplary embodiments.
[0008] A control unit is arranged in the monitoring system or is
associated with the monitoring system in at least some exemplary
embodiments. The control unit is configured and intended to
organize, to control or to regulate a course of a measurement-based
monitoring of the gas composition of air, breathing air or
breathing gases in airplanes or aircraft. The control unit is
preferably configured from components (.rho.C, .mu.P, PC) with
corresponding operating system (OS), memory (RAM, ROM, EEPROM) as
well as SW code, software for process control, control, and
regulation. In at least some exemplary embodiments, additional
electronic components, for example, components for signal detection
(AD.mu.C), signal amplification, for analog and/or digital signal
processing (ASIC), components for analog and/or digital signal
filtering (DSP, FPGA, GAL, .mu.C, .mu.P), and signal conversion
(A/D converter) are assigned to the control unit or are connected
to the control unit in at least some exemplary embodiments.
[0009] In at least some exemplary embodiments, a qualitative and a
quantitative measurement-based detection of a concentration of
oxygen may be made possible in at least some exemplary embodiments.
The concentration of oxygen may be determined in this case by
measurement, for example, in the form of a partial pressure in a
gas mixture of, for example, the breathing air or of the breathing
gas or in the form of a volume concentration or in the form of a
mass per unit volume. In at least some exemplary embodiments, a
qualitative and a quantitative measurement-based detection of a
concentration of carbon dioxide may be made possible by means of
the sensor mechanism in at least some exemplary embodiments. The
concentration of carbon dioxide may be determined in this case by
measurement, for example, in the form of a partial pressure in a
gas mixture, for example, of the breathing air or of the breathing
gas or in the form of a volume concentration or in the form of a
mass per unit volume. In at least some exemplary embodiments, a
qualitative and a quantitative measurement-based detection of a
concentration of carbon monoxide may be made possible by means of
the sensor mechanism. The concentration of carbon monoxide may be
determined in this case by measurement, for example, in the form of
a partial pressure in a gas mixture, for example, of the breathing
air or of the breathing gas or in the form of a volume
concentration or in the form of a mass per unit volume. The sensor
mechanism may have at least one sensor in at least some exemplary
embodiments. The at least one sensor is preferably configured in
this case as an oxygen sensor, as a carbon dioxide sensor or at
least one additional gas sensor, especially carbon monoxide sensor.
In at least some exemplary embodiments, a paramagnetic oxygen
sensor or a measuring module with a paramagnetic oxygen sensor may
be used for the qualitative and quantitative measurement-based
detection of the concentration of oxygen. An electrochemical oxygen
sensor may be used in this case in another advantageous manner. An
oxygen sensor or a measuring module with an oxygen sensor, which
operates according to the principle of luminescence quenching or
fluorescence quenching, may be used in this case in another
advantageous manner. A semiconductor oxygen sensor, preferably in
the form of a so-called MEMS oxygen sensor or a measuring module
with a semiconductor oxygen sensor or with a MEMS oxygen sensor,
may be used in this case in another advantageous manner. An
electrochemical oxygen sensor and/or paramagnetic oxygen sensor or
a measuring module with an electrochemical oxygen sensor and/or
with a paramagnetic oxygen sensor may be used in this case in
another advantageous manner. An electrochemical oxygen sensor
and/or a semiconductor oxygen sensor or a measuring module with an
electrochemical oxygen sensor and/or with a semiconductor oxygen
sensor may be used in this case in another advantageous manner. A
paramagnetic oxygen sensor and/or a semiconductor oxygen sensor
and/or with an electrochemical oxygen sensor or a measuring module
with a paramagnetic oxygen sensor and/or with a semiconductor
oxygen sensor and/or with an electrochemical oxygen sensor may be
used in this case in another advantageous manner. A paramagnetic
oxygen sensor and/or a semiconductor oxygen sensor or a measuring
module with a paramagnetic oxygen sensor and/or with a
semiconductor oxygen sensor may be used in this case in another
advantageous manner. An optical carbon dioxide sensor, preferably
in the form of an infrared optical, a so-called IR carbon dioxide
sensor, or a measuring module with an optical, preferably infrared
optical carbon dioxide sensor, with a so-called IR sensor, may be
used in at least some exemplary embodiments for the qualitative and
quantitative measurement-based detection of the concentration of
carbon dioxide. A semiconductor carbon dioxide sensor, preferably
in the form of a so-called MEMS carbon dioxide sensor or a
measuring module with a semiconductor carbon dioxide sensor or with
a MEMS carbon dioxide sensor may be used in this case in another
advantageous manner. A semiconductor carbon dioxide sensor,
preferably in the form of a so-called MEMS carbon dioxide sensor
and/or an optical carbon dioxide sensor, preferably in the form of
an infrared optical, so-called IR carbon dioxide sensor or a
measuring module with a semiconductor carbon dioxide sensor or a
MEMS carbon dioxide sensor and/or with an optical carbon dioxide
sensor or IR carbon dioxide sensor may be used in this case in
another advantageous manner.
[0010] The measuring modules with at least one oxygen sensor are
also called oxygen measuring modules in the context of the present
invention. The measuring modules with at least one carbon dioxide
sensor are also called carbon dioxide measuring modules in the
context of the present invention.
[0011] The oxygen measuring modules and/or carbon dioxide measuring
modules may also have additional sensors in some embodiments or
additional sensors may also be associated with the oxygen measuring
modules and/or carbon dioxide measuring modules in some embodiments
and/or such additional sensors may be arranged at the modules. The
oxygen measuring module and/or the carbon dioxide measuring module
may optionally be configured in some embodiments such that they are
combined with additional gas sensors and optionally with additional
sensors for the measurement-based detection of measured variables
or substance parameters, for example, pressure, ambient pressure,
airway pressure, mask pressure, density, temperature, thermal
conductivity, thermal capacity, volume flow, mass flow, flow rate,
volumes, or they are configured as an environmental or ambient
analysis module. Thus, a pressure sensor in the monitoring system
may be arranged, for example, as a component of the oxygen
measuring module or of the carbon dioxide measuring module, which
is configured to detect a pressure level in the measured gas line.
In addition, a flow sensor or flow rate sensor in the monitoring
system may be arranged, for example, as a component of the oxygen
measuring module or of the carbon dioxide measuring module, which
is configured for the detection of a flow rate or of a flow in the
measured gas line. Measured values of the flow sensor, flow rate
sensor as well as of the pressure sensor may be made available to
the control unit.
[0012] In some embodiments, the monitoring system or such modules
as gas measuring modules, measuring modules, environmental or
ambient analysis modules, may have at least one gas transport
module. The gas transport module has to this end a gas delivery
device, preferably a pump, with a gas port, which gas delivery
device is configured to deliver a defined quantity of gas from a
measuring point located at a distance from the sensor mechanism or
from the oxygen measuring module, carbon dioxide measuring module
or gas measuring module to the oxygen measuring module, to the
carbon dioxide measuring module or to the gas measuring module or
to the oxygen sensor or to the carbon dioxide sensor in order for
the measurement-based detection of the oxygen concentration and/or
carbon dioxide concentration to be made possible. The pump or the
gas transport module is configured such as to suck in quantities or
partial quantities of breathing gas or breathing air from a
measuring point, especially from the breathing mask and/or from the
cabin or from the cockpit and to deliver it to the monitoring
system or to the oxygen measuring module and/or to the carbon
dioxide measuring module or to the sensor mechanism, especially to
the oxygen sensor and/or to the carbon dioxide sensor. The
breathing mask may be configured, for example, as a partial mask,
half mask or full mask or as a combination of a safety helmet with
a mask. Valves may additionally be arranged in the incoming flow in
front of the pump or in the outgoing flow behind the pump in order
to largely or completely prevent back flows or to avoid unintended
flows or flowthrough. The gas transport module is preferably
connected pneumatically and/or fluidically to the measuring point
in a gas-carrying manner preferably by means of a measured gas line
(sample line). A gas-carrying component is preferably used as a
measuring point in the area of the face, i.e., close to the
mouth/nose area of the aviator, pilot or copilot to monitor the
breathing gas supply of the aviator, pilot or copilot. One end of
the measured gas line is preferably arranged at the mouth/nose
area, for example, at the breathing mask, in order to make possible
a flow of quantities of gas from the mouth/nose area to the gas
transport module of the monitoring system. The other end of the
measured gas line is preferably connected pneumatically or
fluidically to a gas port for an incoming flow into the gas
transport module such that a delivery of quantities of gas or of
partial quantities of breathing gas is made possible, for example,
at a flow rate in the range of 25 mL/min to 250 mL/min by means of
the gas transport module to the oxygen measuring module and/or to
the carbon dioxide measuring module. The gas transport module is
connected to this end pneumatically and/or fluidically to an
additional gas port for the outgoing flow or delivery to the oxygen
measuring module and/or to the carbon dioxide measuring module. The
control unit can control the gas transport module by means of the
flow sensor or flowthrough sensor and it can control, regulate or
set the quantities of gas to be delivered or to be sucked in in the
measured gas line. The control unit can monitor the pressure level
in the measured gas line by means of the pressure sensor and it can
also control, regulate or set it by means of the gas transport
module. If the flowthrough sensor is configured as a pressure
difference sensor GP sensor) of a difference measurement of two
pressure measurement points over a flow diaphragm, a pressure
measurement of the pressure level in the measured gas line can also
be made possible with this sensor with the detection of one of the
two pressure measurement points with reference to the
environment.
[0013] In a preferred embodiment, the gas transport module in the
form of a pump may be arranged at a gas inlet of the monitoring
system. In such an exemplary constellation, the gas transport
module sucks in quantities of gas through the measured gas line
from the breathing mask of the aviator into the monitoring system
and it then delivers these quantities of gas to and through the
sensor mechanism for the determination of the gas concentration.
After flowing through the sensor mechanism, the quantities of gas
enter into the environment through a gas outlet.
[0014] In another preferred embodiment, the gas transport module in
the form of a pump may be arranged at a gas outlet of the
monitoring system. In such an exemplary constellation, the gas
transport module sucks quantities of gas through the measured gas
line from the breathing mask of the aviator into the monitoring
system through the sensor mechanism for the determination of the
gas concentration. After flowing through the pump, the quantities
of gas enter the environment through a gas outlet. With the pump
being arranged at the gas outlet, possible contaminants cannot
reach the sensor mechanism through the pump. Quantities or partial
quantities of breathing gas can be transported via the gas
transport module, especially the pump, via the pneumatic and/or
fluidic connection to the oxygen measuring module and/or to the
carbon dioxide measuring module or to the oxygen sensor and/or to
the carbon dioxide sensor, so that a measurement-based detection of
concentrations of oxygen and/or carbon dioxide is made possible.
The monitoring system is configured in such a construction that it
can be arranged in or at the clothing of the aviator, pilot or
copilot. The measured gas line has a corresponding length, so that
such an arrangement is made possible. Accommodation or arrangement
of the monitoring system in a breast pocket, leg pocket or thigh
pocket of a flight suit (aviator overall) is especially
advantageous. The gas delivery module is configured and constructed
such that quantities of gas can be delivered from the measuring
point to the preferred location of arrangement in a breast pocket,
leg pocket or thigh pocket of the flight suit. The gas transport
module may be configured, for example, as a centrifugal pump, axial
pump, radial pump, reciprocating pump or a diaphragm pump. A pump
with low energy consumption is especially advantageous for use in
the monitoring system for mobile and energy-self-sufficient use. A
piezoelectrically operated pump, also often called piezo pump,
makes possible, for example, an energy-saving use for gas
concentration measurement in the monitoring system. Such a pump is
available commercially, for example, from Murata Manufacturing
Corp. of Kyoto, Japan, as a so-called "piezoelectric blower" or
"microblower" with the names MZB1001T02 as well as MZB 1001. These
pumps do not block the flow even without electrical actuation or
activation, and it is therefore advantageous in case of use for the
monitoring system to provide a valve, which ensures the flow in the
measured gas line in a reliable and reproducible manner and
unambiguously with two states, namely, "release" and "blockage." A
shut-off valve, a so-called "flow-lock valve," which may preferably
be arranged at the gas outlet, is advantageous for the embodiment
with the pump at the gas outlet as well as for the embodiment with
the pump at the gas inlet. The arrangement of the shut-off valve at
the gas outlet of the monitoring system makes possible the use of
the pressure sensor arranged in the interior of the monitoring
system for determining the pressure in the breathing mask of the
aviator by means of a measurement maneuver to determine the
pressure in the breathing mask, because the pressure level in the
interior of the monitoring system corresponds to the pressure level
in the measured gas line as well as to the pressure level in the
breathing mask with the shut-off valve closed in the no-flow state.
A reversing valve, a so-called "3/2-way valve," which may
preferably be arranged at the gas inlet, is advantageous, as an
alternative, for the embodiment with the pump at the gas inlet.
This reversing valve makes it possible, on the one hand, to feed
quantities of gas from the measured gas line into the monitoring
system, and, on the other hand, it can thus also be made possible
to feed quantities of gas from the environment, i.e., from the
cabin of the aircraft. The control unit can simultaneously
determine the pressure level in the breathing mask by means of a
measurement maneuver for determining the pressure in the breathing
mask during the feed of quantities of gas from the cabin.
[0015] An additional gas port with a reversing valve is arranged in
the monitoring system in a preferred embodiment. An additional gas
port with a reversing valve is arranged in or at the gas transport
module in another preferred embodiment. This reversing valve makes
possible a switching between a feed of quantities of gas from the
measured gas line and a feed of quantities of gas by means of the
additional gas port from the environment, for example, from the
cabin of the aircraft. In another preferred embodiment, an
additional pump is arranged in or at the additional gas port. This
additional pump makes it possible to feed quantities of gas by
means of the additional gas port from the environment, for example,
from the cabin of the aircraft. In addition to the shut-off valve
at the gas outlet, an optional reversing valve may be arranged at
the gas inlet for switching between a monitoring of quantities of
gas from the measured gas line from the breathing mask and of
quantities of gas from the cabin for the embodiment with the pump
at the gas outlet. Thus, the control unit is then enabled to carry
out at any time a switching between the feed of quantities of
breathing gas from the breathing mask of the aviator and a feed of
gas from the cabin independently from times at which the pressure
in the mask is determined.
[0016] The control unit may be configured in some embodiments to
determine breathing phase information, i.e., a duration in time of
an inhalation, a duration in time of an exhalation, a ratio (I:E
ratio) of the duration of inhalation to the duration of exhalation,
as well a respiratory frequency of the aviator, pilot or copilot,
from the measured values of the carbon dioxide sensor.
[0017] The sensor mechanism and the control unit may be configured
in at least some exemplary embodiments to detect at least one
environmental parameter and/or at least one operating parameter.
Operating parameters may be, for example, parameters from the
flying operation, parameters from the supply of the aviator, pilot
or copilot with breathing gases, parameters from the control and
regulation of the aircraft or of components of the aircraft. In at
least some exemplary embodiments, the sensor mechanism and the
control unit may be configured to also take into account at least
one environmental parameter and/or to also include it in the
process during the control of the measurement-based monitoring
process.
[0018] The control unit is configured in a preferred embodiment in
conjunction and together with a pressure sensor to determine a
current pressure level in the breathing mask. The aviators (pilots,
copilots) are supplied by means of a breathing mask arranged at the
mouth/nose area during the flying operation of a jet airplane
(jet). The monitoring of the current pressure level in the
breathing mask of the aviator, pilot or copilot is therefore of
particular interest. It can thus be ensured that a sufficient
pressure level of breathing gas is made available by means of the
breathing mask for the aviator, pilot or copilot.
[0019] Embodiments show possibilities of configuring a detection of
pressure levels in the breathing mask by means of the sensor
mechanism and of the control unit and of thus monitoring,
providing, outputting and/or documenting the pressure level in the
breathing mask. The control unit detects a pressure level in the
measured gas line by means of a pressure sensor, which is arranged
in the monitoring system connected pneumatically and fluidically in
a pneumatic system to the components breathing mask, measured gas
line, connection elements and an HME filter element optionally
arranged in a series connection in the measured gas line to detect
a pressure measured value, which indicates a pressure level in the
pneumatic system. In another preferred embodiment for detecting the
current pressure level, a pressure measurement is initiated by the
control unit in a measurement situation during the operation of the
monitoring system, in which no quantities of gas are fed from the
breathing mask to the sensor mechanism with the gas transport
module deactivated and with the pump deactivated, i.e., the gas
concentration measurement by the sensor mechanism is interrupted or
paused at times. The measured value, which indicates the pressure
level in the pneumatic system, corresponds in such a measurement
situation to the current pressure level in the breathing mask. In
addition to the deactivation of the pump, the shut-off valve can be
brought into a closed state in order to prevent any exchange of gas
of the pneumatic system with the environment. A measurement and
checking of the pressure level in the breathing mask can be carried
out intermittently with such an embodiment if the feed of
quantities of gas by the pump is deactivated at defined time
intervals.
[0020] A pressure measurement is initiated by the control unit in
another preferred embodiment for detecting the current pressure
level during the ongoing operation of the monitoring system, in
which quantities of gas are continuously fed from the breathing
mask to the sensor mechanism. A measurement and checking of the
pressure level in the breathing mask can be carried out with such
an embodiment continuously if an adaptation or calibration to
pressure drops of the pneumatic system, which change during the
operation, is carried out with the components breathing mask,
measured gas line, connection elements and the HME filter element
intermittently at different time intervals. An adaptation or
calibration, which can be carried out intermittently or at defined
time intervals, may be configured in such a preferred embodiment by
a measurement maneuver, which is coordinated and carried out by the
control unit in interaction with the gas transport module or the
pump, the shut-off valve and a memory. Such a measurement maneuver
may be carried out from time to time during the flying operation in
order to continuously determine changes in or at the pneumatic
system at defined times in the time course of the operation of the
monitoring system during the mission at the aviator. The
measurement maneuver comprises a measurement-based detection of
pressure levels for zeroing or for offset determination at two
working points. The measurement maneuver is divided into a pressure
measurement of a static pressure level at a working point without a
gas flow in the pneumatic system and into a measurement-based
detection of a dynamic pressure level in the form of a measurement
at another predefined working point with a defined flow in the
pneumatic system. A pressure measured value is detected during the
measurement-based detection of the static pressure level without
gas flow within the pneumatic system with the components breathing
mask, measured gas line, connection elements and an HME filter
element optionally arranged in the measured gas line in a series
connection. Without a gas flow, i.e., with the pump shut off and
with a resulting flow rate of 0.00 mL/min, no pressure drops caused
by components will occur in the pneumatic system between the
breathing mask and the pressure sensor or the pump in the
monitoring system. The HME filter element is used to prevent
moisture from the breathing gas supply with breathing tube and
breathing mask, which moisture is introduced into the measured gas
line by the exhalation of the aviator during the operation, from
entering into the monitoring system for monitoring a gas
composition of breathing gases. Such an HME filter element
(HME=Heat Moisture Exchange) is configured to retain quantities of
moisture. The HME filter element is arranged in a preferred
embodiment in the measured gas line, at the gas inlet or at the gas
transport module. Due to the exhalation of moist breathing gases by
the aviator, quantities of moisture or liquid will continuously
accumulate during the operation in the HME filter element. This
leads to changes in the flow resistance over the duration of the
use during the flying operation with the monitoring system
operating. In addition to the switching off of the pump, the
shut-off valve will advantageously be brought into a closed state
in order to prevent any gas exchange of the pneumatic system with
the environment. The detected pressure measured value without gas
flow in the measured gas line corresponds to a snapshot of the
current pressure in the breathing mask with the shut-off valve
closed and it is stored as a static pressure of the pneumatic
system in a memory. A pressure measured value with a defined
quantity of a gas flow with pressure drops corresponding to this
gas flow at the components of the pneumatic system with measured
gas line, with connection elements and with the optional HME filter
element is detected at the time of the measurement-based detection
of the dynamic pressure level. The detected pressure measured value
with a defined quantity of a gas flow is stored as a dynamic
pressure of the pneumatic system in the memory. A range of 10
mL/min to 400 mL/min can be activated, controlled or regulated by
the control unit as a suitable and defined quantity of the gas flow
in the measured gas line. The pressure measured value with flow
corresponds to the dynamic current total pressure drop of the
pneumatic system. This pressure measured value then corresponds to
the sum of the pressure drops in the pneumatic system, i.e., with
pressure drops over the components such as breathing mask, HME
filter element, measured gas line and connection elements. The
control unit can determine from the difference of the previously
determined static pressure level and the sum of the dynamic
pressure drops the pressure drop attributed to the components as an
offset pressure level in the pneumatic system. Changes in the
differences determined between the dynamic and static pressure
measured values between two or more times at which the measurement
maneuver is carried out make it possible for the control unit to
draw conclusions concerning changes in the pressure drops and
changes in the offset pressure level in the pneumatic system during
the operation. These offset pressure levels in the pneumatic system
and their differences as well as their changes are detected or
determined continuously during the flying operation by the control
unit and are stored in the memory, for example, in the form of a
data set or of a table or as a log file. The control unit is
advantageously configured by means of the measurement maneuver in
this preferred embodiment to determine, subsequently to provide, to
output and/or to store, in the form of data sets or tables, offset
pressure levels determined by a measurement-based detection of
static and dynamic pressure drops over the pneumatic system as
calibration values for a determination of the current mask
pressure. Thus, the measurement maneuver provides trends and
changes of the offset pressure level during the operation of the
monitoring system at the aviator, pilot or copilot during the
mission. It is possible in this manner to determine and to monitor
the particular, currently occurring mask pressure of the aviator
even among components of the pneumatic system which change during
the flying operation. In particular, an increase in the pressure
drop over the HME filter element, which is due to moisture
saturation, can be detected as a change in the offset pressure
level by continual repetitions of the measurement maneuver and it
can be compensated in the calculation of current pressure levels in
the breathing mask. Such repetitions of the checking may take
place, for example, once every 15 minutes to 60 minutes, and a more
frequent performance is not advantageous because the monitoring
concerning the gas concentrations is interrupted or paused for a
short time for the performance of the maneuver. The determination
of the current pressure in the breathing mask can also be carried
out by the control unit during the operation with the pump
activated and with measurement-based detection of the gas
concentrations of oxygen and/or carbon dioxide as well as possibly
other gases or the cabin air on the basis of a use of the offset
pressure level of the components of the pneumatic system, which
offset pressure level was determined last with the measurement
maneuver. The current pressure level present in the breathing mask
is obtained by subtracting the last determined offset pressure
level, which is stored in the memory and is the last determined
offset pressure level provided there, from the current pressure
measured value obtained during the flow through the measured gas
line. The measurement maneuver, which was already described before
for determining the pressure in the breathing mask, will also be
explained in respect to the integration of this measurement
maneuver into the measuring operation of the monitoring system for
the measurement-based detection of the gas concentration,
preferably of carbon dioxide and oxygen, with the functions of the
components involved in that process. The measurement maneuver can
be activated or started at predefined times from the ongoing
measuring operation of the monitoring system. The following steps
are activated, initiated and carried out by the control unit in a
sequence of steps from a start to an end: [0021] a deactivation of
the pump is carried out in a first step, [0022] the shut-off valve
is closed in a second step, [0023] a first measuring operation is
carried out in a third step by the pressure sensor with a pressure
measurement to determine the static pressure level, [0024] the
shut-off valve is opened in a fourth step, [0025] the pump is
activated in a fifth step to deliver quantities of gas at a defined
flow rate in the range of 50 mL/min to 100 mL/min from the
breathing mask through the measured gas line into the monitoring
system to the sensor mechanism; the flow rate is controlled and
monitored in the process by a flow measurement by means of the
flowthrough sensor, [0026] another measuring operation is carried
out in a sixth step by the pressure sensor, i.e., a pressure
measurement is carried out to determine the dynamic pressure level,
and [0027] a determination of a difference value is carried out in
a seventh step with the pressure measured values of the first
pressure measurement and of the additional pressure
measurement.
[0028] The difference value thus determined represents the offset
pressure level and can be provided and used as a calibration value
for the determination of a mask pressure during the further
operation of the monitoring system during the mission of the
aircraft. In optional embodiments of the sequence of steps of the
measurement maneuver, the measurement-based detections of the
static and dynamic pressure level and/or of the flow rates can be
carried out by the control unit in the third, fifth and sixth steps
synchronized with the breathing of the aviator, pilot or copilot.
The pressure measurements and/or the flow measurements can thus
preferably be carried out during inspiratory or expiratory
pauses.
[0029] In a preferred embodiment, the control unit may be
configured to also take information concerning breathing phases of
the aviator into account during the measurement-based detection
and/or determination of the static pressure measured value and/or
of the dynamic pressure measured value during the carrying out of
the measurement maneuver to determine the pressure in the breathing
mask. The detection of the pressure measured values with a
synchronization with the breathing with performance of the measured
value acquisition during pauses between inhalation and exhalation
is advantageous because no pressure effects due to the breathing,
which are superimposed to the static and/or dynamic pressure
levels, can make unfamiliar or influence the pressure measured
value. The synchronization with the breathing can be carried out by
the control unit by means of breathing phase information based on
changes in the concentrations of carbon dioxide and/or oxygen,
which changes are detected by measurement in the monitoring system.
The physiological concentration differences in the oxygen content
in the breathing gas between inhalation (21%) and exhalation (16%)
as well as concentration differences in the carbon dioxide content
between exhalation (.about.5%) and inhalation (<1%) can be used
by the control unit to determine breathing phases. Without such
synchronization of the pressure measurement, a suitable signal
filtering, for example, by means of low-pass filtering
or--preferably sliding--mean value formation of the measured values
of the pressure sensor, is useful in order to remove the components
of the breathing or of the respiratory rate from the pressure
measured values.
[0030] Provisions can therefore be made in an especially preferred
embodiment for the control unit to be configured, together with the
signal processing with the use of suitable signal filtering, to
determine the static and/or dynamic pressure measured values with
removal of signal components induced by the breathing of the
aviator by means of signal filtering. A gas analysis of the cabin
air can advantageously be carried out with the use of the reversing
valve during the time during which the mask pressure is determined.
Predefined values (set points), reference values as threshold
values of the breathing mask pressure can be provided by an
external system, for example, via a data interface. The monitoring
system can then determine an alarm generation situation on the
basis of such values in case of values above or below the threshold
values and provide corresponding alarm signals and/or data. Such a
provision may be carried out, for example, in a wired manner, in a
wireless manner by means of radio transmission, in a wireless
manner by means of infrared transmission to external systems.
Further possibilities for generating an alarm for the aviator are
offered by visual, optical or acoustic signal generation systems,
such as lamps, light-emitting diodes, display units, speakers,
buzzers, horns or comparable elements. Another possibility for
alarm generation for the aviator may be tactile alarm generation,
for example, in the form of a vibration alarm.
[0031] Additional embodiments can show how additional environmental
parameters may be able to be determined by the control unit in
addition to the mask pressure. Environmental parameters include
during the operation of airplanes or aircraft, for example, [0032]
ambient pressure outside the cockpit or cabin of the airplane or
aircraft, [0033] ambient temperature within the cockpit or cabin of
the airplane or aircraft, [0034] gas composition within the cockpit
or cabin of the airplane or aircraft, [0035] absolute and/or
relative humidity within the cockpit or cabin of the airplane or
aircraft, [0036] density and/or ambient pressure within the cockpit
or cabin of the airplane or aircraft, [0037] ambient temperature
within the cockpit or cabin of the airplane or aircraft, [0038] gas
composition within the cockpit or cabin of the airplane or
aircraft, [0039] ambient pressure outside the cockpit or cabin of
the airplane or aircraft, [0040] ambient temperature outside the
cockpit or cabin of the airplane or aircraft, [0041] gas
composition outside the cockpit or cabin of the airplane or
aircraft, [0042] absolute and/or relative humidity outside the
cockpit or cabin of the airplane or aircraft, [0043] density and/or
ambient pressure outside the cockpit or cabin of the airplane or
aircraft, [0044] ambient temperature outside the cockpit or cabin
of the airplane or aircraft, [0045] gas composition outside the
cockpit or cabin of the airplane or aircraft, [0046] pressure
level, pressure changes, pressure changes over time, pressure
differences, pressure fluctuations in the breathing gas, breathing
gas mixture or in the breathing air in the feed line to the
aviator, pilot or copilot, and [0047] pressure level, pressure
changes, pressure differences, pressure fluctuations in the
on-board equipment provided (e.g., gas tanks, pressurized oxygen
cylinders, air intake, gas treatment, filtering) for breathing gas,
breathing gas mixture or breathing air.
[0048] The control unit may be configured in at least some
exemplary embodiments also to take into account at least one
situational parameter during the control of the course of the
measurement-based monitoring and/or to include it in the procedure.
Situational or current situational parameters are defined as
situations and/or states arising from situations during the
operation of airplanes or aircraft.
These include, for example: [0049] a flight direction, [0050] a
flight altitude, [0051] a flight axis position, [0052] a flight
position,
[0053] for example, inverted flying, curve flight, nosedive,
descent, ascent, [0054] a flight velocity, [0055] a horizontal
acceleration, [0056] a vertical acceleration, [0057] a yaw angle or
a roll angle, [0058] a residual oxygen or air reserve, and [0059] a
residual reserve of pressurized oxygen or compressed air.
[0060] The monitoring system may have a data interface in some
embodiments. The data interface may be configured as a
unidirectional or bidirectional data interface and may be
configured, for example, for data supply, data reception, data
exchange or communication with components of the airplane or
aircraft.
[0061] The situational parameters and/or the ambient parameters may
be received and/or provided in at least some exemplary embodiments
by the monitoring system and/or by the control unit by means of the
data interface. In at least some exemplary embodiments, the
situational parameters and/or the ambient parameters may be
detected by measurement by means of additional sensors of the
sensor mechanism, which are arranged in or at the monitoring
system, and be made available to the control unit. Additional gas
sensors, for example, for the measurement-based detection of carbon
monoxide as well as additional gas sensors, e.g., in the form of
electrochemical gas sensors, catalytic gas sensors, optical,
infrared optical gas sensors, photoionization gas sensors, solid
electrolyte gas sensors or semiconductor gas sensors may be used
for this purpose in the sensor mechanism in addition to the sensor
mechanism for the measurement-based detection of oxygen and/or
carbon dioxide, in order to make it possible to monitor the
breathing gas in addition to the measurement-based detection of
concentrations of oxygen and carbon dioxide with respect to other
substances as well, such as hydrocarbons, residues or products of
combustion processes. All additional sensors in the sensor
mechanism may also be provided by pressure sensors, which may be
configured to detect an ambient pressure from the environment,
especially a pressure or a density within and/or outside the
cockpit or cabin of the airplane or aircraft by measurement and to
make it available to the control unit. The additional sensors in
the sensor mechanism may be configured as temperature sensors,
which may be configured and intended for detecting an ambient
temperature of the environment, especially a temperature inside
and/or outside a cockpit or cabin of the airplane or aircraft, by
measurement, and to make it available to the control unit. These
additional sensors in the sensor mechanism may be configured as
humidity sensors for detecting an absolute or relative humidity of
the environment, which may be configured or intended to detect a
humidity in the environment, especially inside and/or outside a
cockpit or cabin of the airplane or aircraft and to make it
available to the control unit.
[0062] In some embodiments, additional sensors at/in the sensor
mechanism in the monitoring system may be provided for detecting
data to determine the situational parameters or they may be
associated with the sensor mechanism, which make it possible for
the control unit to determine a current flight situation with
flight altitude, flight direction, flight velocity, flight
acceleration, flight position with orientation in space and flight
situation or flight maneuver (e.g., ascent, descent, curve flight,
approach for landing, start). For example, pressure sensors,
acceleration sensors, altitude sensors, compass sensors, gyro
sensors, humidity sensors, and temperature sensors are arranged for
this purpose at or in the sensor mechanism or are associated with
the sensor mechanism.
[0063] The sensor mechanism may be arranged in some embodiments
very close to the mouth/nose area in or at the breathing mask.
Depending on the fluidic conditions at the mouth/nose area, an
active transport of breathing gases to the sensor mechanism may be
eliminated in such cases. The breathing gases reach the sensor
mechanism passively, i.e., by diffusion from the mouth/nose area in
the mask. Integration of the sensor mechanism into the breathing
mask in or at parts of the breathing mask may be made possible in
special configurations. Due to the progress being made in
technological development in the area of chip and/or MEMS
technology, miniaturization of elements of the electrochemical,
catalytic or semiconductor sensor mechanisms can be expected in the
near future, and this will then be able to make possible an
integration of the sensor mechanism, preferably oxygen sensor
mechanism, carbon dioxide sensor mechanism and other gas sensors as
well as of additional and optional pressure sensor mechanisms
and/or temperature sensor mechanisms directly at the measuring
point.
[0064] An additional gas port may be provided at the gas transport
module in some embodiments. The additional gas port makes it
possible to connect and to feed quantities or partial quantities of
gas or ambient air from the cabin or the cockpit to the monitoring
system. Gas, quantities or partial quantities from the ambient air
or from the mouth/nose area of the aviator, pilot or copilot, for
example, from the breathing mask can be fed as desired to the pump
or to the gas transport module via a reversing valve (e.g., a
3/2-way valve) or a system of valves.
[0065] An additional pump may be provided in some embodiments and
it may be arranged such that a pump for transporting gas,
quantities or partial quantities from the ambient air to the oxygen
measuring module and/or to the carbon dioxide measuring module or
to the oxygen sensor and/or to the carbon dioxide sensor is
provided and arranged and this additional pump is intended and
arranged for transporting gas, quantities or partial quantities
from the mouth/nose area of the aviator, pilot or copilot, for
example, from the breathing mask, to the oxygen measuring module
and/or to the carbon dioxide measuring module or to the oxygen
sensor and/or to the carbon dioxide sensor. A reversing valve
(e.g., a 3/2-way valve) or a system of valves for switching between
quantities or partial quantities of breathing gas can thus be
eliminated in such an embodiment.
[0066] The control unit may be configured in some embodiments to
control the gas transport module. A control of the gas transport
module may comprise in this case an activation, a deactivation, a
setting, a control or a regulation of the gas transport module. The
setting may comprise especially a setting of speed of rotation,
flow rate and/or pressure level, for example, by means of optical
or electrical control signals (CAN bus, PWM) or electrical control
voltages. A determination concerning a leak present in the measured
gas line can also be carried out in one variant of such embodiments
on the basis of the detection of gas concentration values and/or
pressure measured values, for example, also on the basis of
pressure differences between the mask and the cockpit.
[0067] The control unit may further be configured in some
embodiments also to take into account and/or to include in the
control at least one ambient parameter or at least one situational
parameter in the control of the gas transport module. Such a taking
into account may comprise especially an adaptation of activation,
deactivation, speed of rotation, flow rate and/or pressure level of
the gas delivery module. It can thus be made possible to deactivate
the gas transport module during certain flight maneuvers, for
example, during an ascent, descent or curve flight and/or
optionally to activate it with an increased flow rate after the end
of the maneuver.
[0068] In at least some exemplary embodiments, the monitoring
system and/or the control unit may be configured for a
determination and/or detection of an alarm situation and for
organizing an alarm generation or for sending an alarm and/or for
providing an alarm signal. The control unit can determine and/or
detect an alarm situation and trigger an alarm generation and/or
provide an alarm signal, for example, at the data interface or at
another data interface on the basis of measured values of the
sensor mechanism and/or by means of information provided for the
data interface. The alarm generation may take place as a visual
and/or acoustic and/or tactile alarm generation. A visual alarm
generation may take place, for example, in the form of a white
and/or colored lighting device (LED, stroboscope) or of a text
output (LCD, LED, display). Such an alarm generation may also be
carried out visually by means of a suitable visualization device at
or in a face mask or breathing mask, for example, as a display on
an in-mask display or head-up display. An acoustic alarm generation
may be carried out, for example, in the form of a speech output or
by means of an acoustic alarm generator (horn, siren). A tactile
alarm generation may be carried out, for example, in the form of a
vibration alarm to equipment of the aircraft, such as seat
surfaces, control elements (pedals, handles) as well as pieces of
equipment (breathing mask, breathing tube) or clothing (suit, vest,
parachute, shoes) of the aviator, pilot or copilot.
[0069] In some embodiments, the control unit can also take into
consideration an ambient parameter and/or a situational parameter
and/or include it in the organization of the alarm generation
during the organization of the alarm generation or alarm and/or
during the provision of the alarm signal. It can thus be made
possible in an advantageous manner that relevant alarm information,
which is prioritized according to relevance, can be provided for
the aviator, pilot or copilot in a consolidated or compact manner
concerning the situation of the measurement-based detection in the
breathing gas with reference to the situation in the environment
(temperature, gas composition in the breathing air) and in
reference to the mission situation or to maneuver situation of the
airplane (start phase, landing approach, in-flight refueling,
descent, curve flight, ascent). In a special embodiment, the
control unit can also take into consideration an ambient parameter
and/or a situational parameter and also include it in an adaptation
of the signal processing during the performance of the signal
processing and/or signal filtering of the measured values of the
sensor mechanism.
[0070] In some exemplary embodiments, the control unit can use
during the organization of the alarm generation predefined
threshold values, which may be stored for certain values of gas
concentrations, especially concentrations of oxygen or carbon
dioxide or carbon monoxide, in the memory of the monitoring
system.
[0071] On the basis of current concentration measured values, which
were obtained in the past and are in the form of a trend monitoring
of oxygen and carbon dioxide, and by means of a suitable decision
matrix or algorithms specially adapted to the problem, teachable or
self-learning algorithms (SVM, Random Forest, AI, Deep Learning,
PCA), the control unit can apply in some embodiments a kind of
early warning system for detecting hypoxia, possibly with an alarm
management adapted to this for the onset of a developing hypoxia.
In a special situation, the control unit can also take into
consideration an ambient parameter and/or a situational parameter.
In a special embodiment, the control unit may also take into
consideration in the early warning system for the detection of
hypoxia additional physiological data of aviators, pilots and
copilots, for example, EKG, heart rate, heart rate variability,
oxygen saturation in the blood, body temperature, which data were
assigned, for example, by means of the data interface or by the
monitoring system.
[0072] In some embodiments, such modules as gas measuring modules,
measuring modules, environmental or ambient analysis modules, may
have at least one energy storage device, e.g., a primary cell or a
rechargeable battery. For example, types of lithium ion batteries,
nickel-metal hydride batteries or nickel-cadmium batteries are
known as types of rechargeable batteries. For example, types of
alkali-manganese batteries, silver oxide-zinc batteries, lithium
batteries and aluminum-air batteries are known as types of primary
cells.
[0073] Battery charging systems and/or battery management systems
for monitoring battery charge and/or battery state as well as
interfaces for supplying the battery charging systems and/or
battery management systems with charging electrical energy may
usually also be integrated additionally in the monitoring system in
embodiments with rechargeable batteries. Battery management systems
usually have interfaces for communication to the outside, in order,
for example, to be able to provide data or information on the state
of the battery, and such interfaces may have a wired (e.g., CAN
bus), contactless (e.g., RFID, NFC), wireless (e.g., Bluetooth) or
infrared optical (e.g., IrDA) configuration. In addition, such
modules as gas measuring modules, measuring modules, environmental
or ambient analysis modules may have additional components, for
example, components for signal detection (AD.mu.C), signal
amplification, for analog and/or digital signal processing (ASIC);
components for analog and/or digital signal filtering (DSP, FPGA,
GAL, .mu.C, .mu.P), signal conversion (A/D converters), components
(.mu.C, .mu.P) for controlling, regulating, components (.mu.C,
.mu.P) for process control of the operation and for user
interaction; input and output interfaces, user interface with at
least one operating element and/or with at least one display
element. The at least one operating element as well as the at least
one display element may be arranged in or at the monitoring system
or may be associated with the monitoring system.
[0074] For example, an operation with beginning (start, activation)
or end (stop, deactivation) of the monitoring system, a selection
between different modes of operation of the monitoring system,
performance of maintenance, adjustment or calibration processes can
be made possible for the user in some embodiments by means of the
at least one operating element.
[0075] The user can be enabled in some embodiments by means of the
at least one display element to be informed of events, situations,
current measured values and/or measured values obtained in the
past, which were detected and provided by measurement by means of
the sensors or measuring modules, especially of the oxygen sensors
and/or of the carbon dioxide sensors or of the oxygen measuring
modules and/or carbon dioxide measuring modules. In addition,
measured variables derived from the measured values, for example,
maximum or minimal values, mean values, trends, statistics, events,
alarm situations, may be provided for the user by means of the
display elements. In addition, general information on the current
operating state of the monitoring system, such as the state of the
battery, residual battery life, maintenance information,
information on the monitoring system itself, such as type, name,
variant, version, serial number, initial start-up, expected
maintenance intervals, status data, operating state (ready, in-OP,
Stand-by), information on malfunctions, error memory, as well as
operating instructions, may be provided for the user by means of
the display elements.
[0076] The display elements may be configured as graphic user
interface (graphical user interface, GUI) in some embodiments.
[0077] In addition to the display elements, input elements may be
provided in some embodiments. The input elements may be configured
as mechanical or touch-sensitive buttons or switches, rotary
controls or slide controls as well as in the form of a graphic user
interface (graphical user interface, GUI). Display elements may be
configured in some embodiments such that they are combined with
input elements. In an embodiment with a touch-sensitive display
(touch screen), there are, for example, possibilities for designing
changeable display possibilities and operating possibilities, e.g.,
a use of gestures (wiping, pulling) in order thus to vary the type
of the display, for example, in order to enlarge or to reduce
display elements (zoom function). The combination of display
elements with input elements may preferably be configured as a
graphic user interface (graphical user interface, GUI, touch
pad).
[0078] It is possible in some embodiments to provide an input
element, which makes it possible for the user or operator of the
monitoring system to initiate, annotate, trigger, start or end
defined actions or states at the monitoring system. Such an input
element may be configured, for example, as an annotation button
and/or as a panic button, which can preferably be operated by
actuation by hand. As an alternative, operation with speech command
may also be possible, in which case the annotation button and/or
the panic button is equipped correspondingly with devices for
speech detection, speech processing and speech recognition with
command detection.
[0079] The input element may also be complemented in other
alternative embodiments by an acceleration sensor or may be
configured by such an acceleration sensor. For example, data or
measured values of an acceleration sensor, which is provided as a
component of an additional sensor mechanism at/in the sensor
mechanism in the monitoring system for detecting data for
determining situational parameters, may also be used for this
purpose by the control unit in order to detect by measurement a
current flight situation with flight altitude, flight direction,
flight velocity, flight acceleration, flight position with
orientation in space and flight situation or flight maneuvers
(e.g., ascent, descent, curve flight, landing approach, start) in
the monitoring system. As an alternative, an additional 2-axis or
3-axis acceleration sensor, which represents a functionality of an
input element in conjunction with the control unit, may be arranged
in or at the monitoring system. Movements or excursions of the
monitoring system, movements or excursions of a housing of the
monitoring system, as well as mechanical, tactile stimuli or
tactile stimulations can be detected by means of sensors by means
of the acceleration sensor and they can be made available as
measured values or data to the control unit. Mechanical or tactile
stimuli or stimulations are sent from the aviator, pilot or copilot
to the acceleration sensor as a force action, energy feed or force
feed in the direction of at least one of the directions or axes
detectable in a sensor-based manner by the acceleration sensor in
the form of actuation acting on the monitoring system by means of
movements of the hand, in the form of application of pressure, in
the form of the action of an impact (push, hit, tapping). This is
made advantageously possible for the aviator, pilot or copilot
especially if the monitoring system is arranged as a mobile module
in a closed pocket in or on the clothing, for example, on or in a
vest, jacket or a suit. The force feed may thus take place as an
actuating activity through the clothing to the acceleration sensor
in the monitoring system. The use of the acceleration sensor as an
input device or input element makes possible an actuation or
operation of the monitoring system by the aviator, pilot or copilot
during the mission when he cannot reach other input elements at the
monitoring system configured as a mobile module. This happens, for
example, when the monitoring system is arranged as a mobile module
in a pocket in or on the clothing. The acceleration sensor thus
offers an alternative to an operation of the monitoring system by
means of a manual button or of a manual switching element. A
control unit may be used for the analysis of the measured values or
data of the acceleration, but it is also possible to provide an
additional unit, which is equipped in the monitoring system to
detect and analyze data of the acceleration sensor. Such an
analysis of the data of the acceleration sensor is based
essentially on time measurements. An analysis can be carried out by
means of time measurements in conjunction with threshold values for
the measured values or data of the acceleration sensor concerning
the duration of the tactile stimulation as well as concerning
durations between two or more tactile stimulations of the
acceleration sensor. The control unit may be configured in an
exemplary embodiment to detect a first-time force action or force
feed to the acceleration sensor by means of a comparison with a
threshold value on the basis of the measured values or data of the
acceleration sensor. If a measured value of the acceleration sensor
is exceeded in respect to a predefined threshold value for a first
predefined duration, the control unit interprets this situation as
a first force action in the direction of at least one of the
directions or axes detectable in a sensor-based manner by the
acceleration sensor. An indicator is thus obtained for a start of
an input activity of the aviator by means of a movement of the hand
as an input operation. If the measured values of the acceleration
sensor are subsequently exceeded once again for a second predefined
time period for a second predefined threshold value, the control
unit interprets this situation as the end of the first force
action. If a measured value of the acceleration sensor is then
exceeded within a third predefined duration in respect to the first
predefined threshold value for the first predefined duration, the
control unit interprets this situation as a further force action in
the direction of at least one of the directions or axes detectable
in a sensor-based manner by the acceleration sensor. An indicator
is thus obtained for a continuation of the input activity of the
aviator. If values below the second predefined threshold value are
then obtained for a second predefined time period from measured
values or data of the acceleration sensor, the control unit
interprets this situation as the end of the further force action.
If no further force actions on the acceleration sensor are detected
and recognized within a fourth predefined duration, an indicator is
obtained for the end of the input activity of the aviator. With
this type of analysis the control unit is configured and able to
detect and recognize an input activity of a "double tap" by a
movement of the hand of the aviator by means of an analysis of the
measured values of the acceleration sensor concerning the first and
second threshold values and of the first, second, third and fourth
durations during the operation of the monitoring system and it can
then trigger further actions based on this in or at the monitoring
system. Such actions may correspond in terms of their manner of
functioning, for example, to functions of an annotation button
and/or of a panic button.
[0080] In addition to the "double tap," the configuration of the
control unit may be expanded in respect to the analysis in some
embodiments such as to make possible inputs by a "triple tap" or
"quadruple tap" as well. A simple coding is obtained in this manner
for inputs effected by means of the acceleration sensor, so that
the control unit can make a distinction between different input
situations by means of a case differentiation between "double tap,"
"triple tap" or "quadruple tap." It is also possible, in principle,
to configure a "single tap," and the duration of the stimulation,
which the "single tap" indicates, would be set now in such a manner
that possibilities of confusion with other stimulations by the
aviator, the aircraft or the equipment are ruled out.
[0081] In addition to the analysis of durations of the tactile
stimulations, the configuration of the control unit may
additionally also include in the analysis in some embodiments
differences of durations between the tactile stimulations of the
acceleration sensor. These differences can then be used by the
control unit, in addition to analyses of forms of "multiple
tapping," to increase the number of events that can be
distinguished from one another, for example, by a distinction
between a "short pause" and a "long pause" as durations between the
tactile stimulations of the acceleration sensor. A type of Morse
code is thus obtained due to this variation of pause lengths during
the analysis of the tactile stimulations, which offers a further
possibility for coding events with the acceleration sensor as the
input element.
[0082] Possibilities and advantages are consequently obtained due
to the fact that when different input situations are distinguished
with assignment to acts or actions triggered with the input, the
aviator, pilot or copilot can start, for example, a measurement
maneuver by hand with the acceleration sensor as the input element
during the flying operation, he can make an entry (annotation) or
set a time mark in a log book or can mark a special health
situation, e.g., a sensation of dizziness during the data recording
or data storage, without having to operate a button or switch at
the monitoring system with visual contact with the monitoring
system. A measurement maneuver may be, for example, a measurement
maneuver to determine static and dynamic pressure levels in the
pneumatic system or a measurement maneuver to activate the
reversing valve to detect gas concentrations in the cabin.
[0083] In some embodiments, a memory for storing measured values of
measured variables derived from measured values, for example,
maxima or minima, mean values, trends, statistics, events and alarm
situations may be arranged in or at the monitoring system or may be
associated with the monitoring system. Such a memory may be
configured as a volatile or non-volatile memory (RAM, ROM, EEPROM)
and may be configured either as a fixed component of the monitoring
system or also as a removable and/or portable memory module (USB
stick, SD card). The memory may be used for data recording or data
storage of inputs made by means of the input element and provide to
this end functions of a log book or flight recorder. In an
embodiment with tables, lists and data sets, the log book may
advantageously receive an analysis of gas concentration measured
values, flow measured values, pressure measured values, temperature
measured values over time with assignment to a time and marking
(annotation), further events or manual inputs by means of the input
element and keep them available and provide them for a simultaneous
or subsequent analysis. When the events are entered, measured
values or measured signals of the acceleration sensor may be added
in order to put the respective marks/notation made in the log book
by the pilot into a context with flight situations or with flight
maneuvers for a real-time or later analysis. When entering the
events, measured values or measured signals of an altitude sensor
may be added in order to put the respective marks/notation made by
the pilot in the log book into a context with flight situations
(flight altitude) for a real-time or later analysis. When entering
the events, measured values or data of the gas sensor mechanism may
be added in order to put the mark/notation made by the pilot in the
log book into a context with the gas supply (CO.sub.2, O.sub.2) for
a real-time or later analysis.
[0084] In a special configuration of some embodiments, the control
unit may be configured to also take into consideration an
environmental parameter and/or a situational parameter when the
signal processing and/or signal filtering is carried out and/or to
include it in the adaptation of the signal processing.
[0085] The control unit may be configured in some embodiments to
use predefined threshold values, which may be stored for defined
values of gas concentrations, especially concentrations of oxygen
or carbon dioxide and carbon monoxide, in the memory of the
monitoring system during the organization of the alarm
generation.
[0086] The control unit may be configured in some embodiments to
employ an early warning system for the detection of hypoxia on the
basis of current and past measured values of the sensor mechanism,
for example, in the form of a trend monitoring of concentrations of
oxygen and/or carbon dioxide, [0087] by means of a decision matrix,
[0088] or by means of specially adapted algorithms, and [0089] or
by means of teachable or self-learning algorithms (e.g., SVM,
Random Forest, AI, Deep Learning, ICA, PCA).
[0090] The control unit may also take into account in this case an
environmental parameter and/or a situational parameter in special
configurations of some embodiments.
[0091] In other special configurations of some embodiments, the
control unit may use an alarm management adapted to the early
warning system. In a special configuration of some embodiments, the
control unit may be configured to take into consideration further
physiological data of aviators, pilots and copilots, which were
provided, for example, by means of the data interface or by the
monitoring system, for example, EKG, heart rate, heart rate
variability, oxygen saturation in the blood and body temperature,
in the early warning system for the detection of hypoxia.
[0092] Further exemplary embodiments create processes for the
operation of a monitoring system.
[0093] In some embodiments of the process for operating a
monitoring system, the control unit performs in a first step an
activation of the sensor mechanism of the monitoring system, and
preparations are made for data storage along with initialization of
a memory in a second step. Measurement-based detection of measured
values of the sensor mechanism of the monitoring system is carried
out with a time control in a third step. Data storage of the
measured values is carried out in the memory with corresponding
time information in a fourth step. The third and fourth steps are
continued continuously by the control unit until the process for
operating a monitoring system is ended.
[0094] In some embodiments of the process for operating a
monitoring system, an additional storage of situational parameters
and/or environmental parameters can be made possible during the
data storage of the measured values of the sensor mechanism with
the corresponding time information in the memory.
[0095] In some embodiments of the process for operating a
monitoring system, an additional detection of measured values of
the sensor mechanism, which detection depends on the time control,
can be made possible when an input element is activated by a
user.
[0096] Further actions improving the present invention appear from
the following description of some exemplary embodiments of the
present invention, which are shown in the figures. All the features
and/or advantages, including design details and arrangements in
space, which appear from the claims, from the description or from
the drawings, may be essential for the present invention both in
themselves and in the different combinations. The various features
of novelty which characterize the invention are pointed out with
particularity in the claims annexed to and forming a part of this
disclosure. For a better understanding of the invention, its
operating advantages and specific objects attained by its uses,
reference is made to the accompanying drawings and descriptive
matter in which preferred embodiments of the invention are
illustrated.
BRIEF DESCRIPTION OF THE DRAWINGS
[0097] In the drawings:
[0098] FIG. 1a is a schematic view showing a monitoring system with
a sensor mechanism;
[0099] FIG. 1b is a schematic view showing the monitoring system
with a sensor mechanism;
[0100] FIG. 2a is a schematic view showing a monitoring system
according to FIG. 1a, 1b with a measurement functionality for
oxygen and carbon dioxide;
[0101] FIG. 2b is a schematic view showing a monitoring system
according to FIG. 1a, 1b with the measurement functionality for
oxygen and carbon dioxide;
[0102] FIG. 3 is a schematic view showing an expansion of the
variants according to the monitoring systems according to FIGS. 1a,
1b, 2a, 2b;
[0103] FIG. 4 is a schematic view showing one of two variants of
the monitoring systems according to FIGS. 1a, 1b, 2a, 2b, 3 with
additional sensor mechanisms;
[0104] FIG. 5 is a schematic view showing another of two variants
of the monitoring systems according to FIGS. 1a, 1b, 2a, 2b, 3 with
additional sensor mechanisms;
[0105] FIG. 6 is a schematic view showing a variant of the
monitoring system according to FIG. 3;
[0106] FIG. 7 is a schematic view showing another variant of the
monitoring system according to FIG. 3;
[0107] FIG. 8 is a schematic view showing an alternative variant of
the monitoring system according to FIG. 6; and
[0108] FIG. 9 is a schematic view showing a flow chart for
determining a pressure in a breathing mask.
DESCRIPTION OF PREFERRED EMBODIMENTS
[0109] Referring to the drawings, FIGS. 1a, 1b show a monitoring
system 100, which is connected with a measured gas line 10 to a
breathing mask 20 of a person 99. Identical elements in FIGS. 1a,
1b are designated by the same reference numbers in FIGS. 1a, 1b.
The person 99 in this FIG. 1 is an aviator (pilot, copilot) or
passenger of an airplane, especially of a jet plane (jet). The
breathing mask 20 has a gas port 21, a connection element 23 as
well as hose lines 24, 25. The hose lines 24, 25 are used to remove
and feed breathing gases to the person 99. The hose lines are shown
in this FIG. 1a as two separate hose lines 24, 25. As is shown in
FIG. 1b, embodiments with a connection element 23', in which
embodiments only one hose line 25 is present for supplying
breathing gas for inhalation, and the exhalation takes place via an
exhalation valve 29 in the breathing mask 20 to an environment, are
also possible. Another possibility is offered by an embodiment of a
coaxial hose system, which has two hose lines 24, 25 as a common
element. The removal and feed of breathing gases into the airplane
or aircraft and the devices or elements necessary therefor for
making the breathing gas available are not shown in this FIG. 1a
and in the other figures for the sake of clarity. The monitoring
system 100 has operating elements 40, display elements 44, at least
one gas delivery module 50, and a sensor mechanism 60 with at least
one sensor 66. The gas delivery module 50 is preferably configured
as a pump PM, more preferably as a piezoelectric pump PM. In
addition, the monitoring system 100 has a control unit 70.
[0110] The operating elements 40, the display elements 44, the
sensor mechanism 60, and the gas delivery module 50 are connected
to the control unit 70 via signal and data lines or control lines.
These control lines or signal and data lines may be configured, for
example, as a bus system (CAN) or network. These control lines or
signal and data lines are not shown in FIG. 1a as well as in the
other figures for the sake of clarity. The control unit 70 is
configured and intended to control and/or to actuate the gas
delivery module 50 such that a delivery of breathing gases from the
breathing mask 20 through the measured gas line 10 and through a
gas inlet 51 to the sensor mechanism will take place. A quantity or
partial quantity of breathing gas is thus then available to the at
least one sensor 66 in the gas sensor mechanism 60 in order to
detect it by measurement and/or to analyze it and to make it
available to the control unit 70 as measured values. The control
unit 70 makes it possible to analyze and process the measured
values and to display them at least on partial elements of the
display elements 44.
[0111] FIGS. 2a, 2b show monitoring systems 100, 110 according to
FIGS. 1a, 1b with the peculiar feature that the sensor 66 in the
sensor mechanism 60 is configured as an oxygen sensor 68 and, in
addition, an additional sensor acting as a carbon dioxide sensor 64
is likewise arranged in the sensor mechanism 60. Identical elements
in FIGS. 1a, 1b, 2a, 2b are designated by the same reference
numbers in FIGS. 1a, 1b, 2a, 2b. FIG. 2a shows a variant 110 of a
monitoring system according to FIG. 2a with an oxygen sensor 68 and
with a carbon dioxide sensor 64, wherein the monitoring system 110
is arranged without a measured gas line 10 directly at the
breathing mask 20 or is configured as a part of the breathing mask
20. A pump PM, as in the variants according to FIGS. 1a, 1b, 2a for
delivering quantities of breathing gas from the breathing mask 20
to the sensor mechanism 60 may optionally be eliminated. In case
quantities of gas are optionally also to be delivered from the
cabin or from the cockpit to the sensor mechanism, an optional pump
56 is also arranged in or at the sensor mechanism in the
arrangement according to FIG. 2b. The arrangement of such an
optional pump 56 in the monitoring system 110 is not shown for the
sake of clarity. An energy storage device 85 is also shown as an
example in FIG. 2b, and it is also an optional component of the
embodiments according to FIGS. 1a, 2a, 3, 4, 5 in a similar
configuration. Such an energy storage device 85, configured as a
primary cell or chargeable or rechargeable battery (rechargeable
battery, storage battery), has a suitable configuration for
supplying the various components (60, 70, 40, 44, 75) of the
monitoring systems 110, 108 (FIG. 4), 109 (FIG. 5), 100 (FIG. 1a,
FIG. 1b, FIG. 2a, FIG. 3) with electrical energy. An optional
embodiment with an additional display element 45 arranged at or in
the mask 20 is shown in FIG. 1b, and there also is a similar
configuration as an optional component of the configurations
according to FIGS. 1a, 2a, 3, 4, 5. This additional display element
45 is connected to the control unit 70 by means of signal or data
lines, not shown for the sake of clarity. This additional display
element may be configured, for example, in the form of an in-mask
display or head-up display. FIG. 2a additionally shows a data
interface 90, which may be configured, on the one hand, to receive
data from the outside and then to provide these data for the
control unit 70. The data lines belonging to the data interface are
not shown in FIG. 2a as well as in the other figures for the sake
of clarity. On the other hand, for example, measured values of the
monitoring system 100 or of the sensor mechanism 60 can be sent to
the outside by means of the data interface 90. Current
environmental parameters or situational parameters on the situation
of the airplane or aircraft can thus be received via this data
interface 90, for example, from components of the airplane or
aircraft, and made available to the control unit 70 for being taken
into consideration in the processing of measured values and/or in
the control of the pump PM 50. Furthermore, measured values and/or
measured variables derived from the measured values or parameter as
well as information or state data may be made available by the
control unit 70 by means of the data interface to components of the
airplane or aircraft. It is possible in this manner, for example,
to display measured values and/or measured values derived from the
measured values or parameters as well as information or state data
on external display elements of the airplane or aircraft. The data
interface may have a unidirectional or bidirectional configuration,
for example, a wired (CAN bus, LAN, Ethernet, RS485, NMEA183) or
wireless (WLAN, Bluetooth, NFC) configuration. The following
parameters shall be mentioned, for example, as current
environmental parameters for an environmental situation of the
airplane or aircraft: [0112] ambient pressure outside the cockpit
or cabin of the airplane or aircraft, [0113] ambient temperature
within the cockpit or cabin of the airplane or aircraft, [0114] gas
composition within the cockpit or cabin of the airplane or
aircraft, [0115] absolute and/or relative humidity within the
cockpit or cabin of the airplane or aircraft, [0116] density and/or
ambient pressure within the cockpit or cabin or the airplane or
aircraft, [0117] ambient temperature within the cockpit or cabin of
the airplane or aircraft, [0118] gas composition within the cockpit
or cabin of the airplane or aircraft, [0119] ambient pressure
outside the cockpit or cabin of the airplane or aircraft, [0120]
ambient temperature outside the cockpit or cabin of the airplane or
aircraft, [0121] gas composition outside the cockpit or cabin of
the airplane or aircraft, [0122] absolute and/or relative humidity
outside the cockpit or cabin of the airplane or aircraft, [0123]
density and/or ambient pressure outside the cockpit or cabin of the
airplane or aircraft, [0124] ambient temperature outside the
cockpit or cabin of the airplane or aircraft, [0125] gas
composition outside the cockpit or cabin of the airplane or
aircraft, [0126] pressure level, pressure changes, pressure-time
curve, pressure differences, pressure fluctuations in the breathing
gas, breathing gas mixture or in the breathing air in the feed line
to the aviator, pilot or copilot, [0127] pressure level, pressure
changes, pressure differences, pressure fluctuations in the
on-board equipment provided (e.g., gas tanks, pressurized oxygen
cylinders, air intake, gas processing, filtering, gas delivery) for
breathing gas, breathing gas mixture or breathing air.
[0128] For example, the following parameters shall be mentioned as
situational or current situational parameters of the situation of
the airplane or aircraft: [0129] a flight direction, [0130] a
flight altitude, [0131] a flight axis position, [0132] a flight
position,
[0133] for example, inverted flying, curve flight, nosedive,
descent, ascent, [0134] a flight velocity, [0135] a horizontal
acceleration, [0136] a vertical acceleration, [0137] a yaw angle or
a roll angle, [0138] a residual oxygen or air reserve, and [0139] a
residual pressurized oxygen gas or compressed air reserve.
[0140] FIG. 3 shows a monitoring system 100 according to FIG. 1a,
1b, 2a with the peculiar feature that an input element 80 with a
signal or data connection to the control unit 70 is arranged at the
monitoring system. Identical elements in FIGS. 1a, 1b, 1c, 2, 3 are
designated by the same reference numbers in FIGS. 1a, 1b, 1c, 2, 3.
It is made possible to the aviator, pilot or copilot via the input
element 80 to mark certain events or situations of the flying
operation, as well as certain personal events, for example, events,
situations or symptoms related to health, such as fever, racing
heart or a feeling of dizziness, during the course of the mission.
This marking can be used by the control unit 70 to combine the
events or situations with time information and then to store the
combination of time information, event or situation in a memory 75.
The memory 75 may be configured as a volatile or non-volatile
memory (RAM, ROM, EEPROM) and be arranged either as a fixed
component or as a removable memory module (USB stick, SD card) in
or at the monitoring system 100, 110 (FIG. 2b). A provision and/or
an exchange of the data may also be made possible with an external
analysis unit, not shown in the figures, for example, by means of a
data interface 90 in a configuration similar to that shown and
described in FIG. 2b. This input element 80 can thus be used to
complement the detected measured values of the sensor mechanism 60
and the events and situations of the flying operation by additional
information, which is made available by means of the input element
of the aviator, pilot or copilot, and to provide it with time
information, for example, in the form of a time stamp. It is also
possible, however, to configure the input element as a panic
button, which makes it directly possible to the aviator, pilot or
copilot to make themself noticeable in a situation that is a
special situation based on his own perception, for example, in a
situation with a special, objectively or subjectively perceived
danger situation or in a risk situation. The marked measured values
and/or events, situation and also the special situations can be
made directly available to the direct external outside environment
for example, by means of the data interface 90, and they can
possibly be transmitted, likewise directly (on-line), via a
communication system of the airplane or aircraft, to a ground
station or to other airplanes or aircraft. Furthermore, an analysis
of the marked measured values and/or events, situations and special
situations later after the mission (off-line) can be made possible
by means of the memory 75 and/or the data interface 90.
[0141] FIGS. 4 and 5 show variants of the monitoring system 100,
110 according to FIGS. 1a, 1b, 2a, 2b, 3 with additional components
of the sensor mechanism 60. The corresponding control lines or
signal and data lines for the additional sensors of the sensor
mechanism 60 are not shown in FIGS. 4 and 5 for the sake of
clarity. Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5 are
designated by the same reference numbers in FIGS. 1a, 1b, 1c, 2, 3,
4, 5. These additional sensors in the sensor mechanism 60 may be
used for determining current environmental parameters within and/or
outside the cockpit or cabin of the airplane or aircraft and/or for
determining current situational parameters and situations as well
as for determining physical properties for an additional
determination of the composition of the breathing gas. The
following additional sensors, which shall also be considered to
represent optional possibilities of configuration for FIGS. 1a, 1b,
2a, 2b, 3, 5, shall be shown as examples as additional components
of the sensor mechanism 60 in the monitoring system 108 in FIG. 4:
[0142] at least one acceleration sensor 61
[0143] in the form of a 2-axis or 3-axis acceleration sensor
(accelerometer), [0144] at least one compass sensor 62,
[0145] for example, an electronic compass,
[0146] gyro compass or fluxgate compass, [0147] at least one
altitude sensor 58, and [0148] at least one gyro sensor 63.
[0149] The following additional sensors, which should also be
considered to be optional possibilities of the configuration for
FIGS. 1a, 1b, 2a, 2b, 3, 4, are shown as examples in FIG. 5 as
additional components of the sensor mechanism 60: [0150] at least
one temperature sensor 69, 69', [0151] at least one pressure sensor
67, 67', [0152] at least one humidity sensor 59, 59'.
[0153] The additional sensors in the sensor mechanism 60 may be
configured as pressure sensors, which may be configured and
intended to detect by measurement an ambient pressure from the
environment, especially a pressure or a density within and/or
outside the cockpit or cabin of the airplane or aircraft and to
make it available to the control unit 70. The additional sensors in
the sensor mechanism 60 may be configured as temperature sensors,
which may be configured and intended to detect by measurement an
ambient temperature in the environment, especially a temperature
within and/or outside the cockpit or cabin of the airplane or
aircraft and to make it available to the control unit 70. These
additional sensors in the sensor mechanism 60 may be configured as
humidity sensors for detecting an absolute or relative humidity of
the environment, which may be configured and intended to detect by
measurement a humidity in the environment, especially within and/or
outside the cockpit or cabin of the airplane or aircraft and to
make it available to the control unit 70. The additional sensors in
the sensor mechanism 60 may be configured as at least one
additional gas sensor 65 for detecting a gas composition in the
environment, which may be configured and intended for detecting by
measurement a gas composition in the environment, especially within
and/or outside the cockpit or cabin of the airplane or aircraft and
to make it available to the control unit 70. Electrochemical gas
sensors, catalytic gas sensors, optical, infrared optical gas
sensors, photoionization gas sensors, solid electrolyte gas sensors
or semiconductor gas sensors may be used as other gas sensors in
order to make it possible to also monitor the breathing gas
concerning additional substances, such as carbon monoxide,
hydrocarbons, residues or products of combustion processes, in
addition to the measurement-based detection of concentrations of
oxygen and carbon dioxide. A reversing valve 55 shown in FIG. 4,
configured, for example, as a valve module or as a part of a valve
module, makes possible the switching of quantities or partial
quantities of gas samples between the gas inlet 51 and another gas
port 52. It is thus made possible to deliver breathing gas from the
breathing mask 20 to the sensor mechanism 60 by means of the pump
PM 50, on the one hand, but it is also possible, in addition, to
deliver quantities of gas or gas mixture from an environment 5 to
the sensor mechanism 60 by means of the pump PM and to detect it by
measurement by means of the sensor mechanism 60. The reversing
valve 55 is controlled by the control unit 70. Outside air can thus
be fed from the outside of the airplane or aircraft or inside air
can be fed from the cabin or cockpit of the airplane or aircraft
via the additional gas port 52 and monitoring of gas concentrations
in the breathing mask 20, cockpit, cabin or outside air can
alternatingly be made possible, with control by the control unit
70.
[0154] The additional sensors 59', 64', 68', 69', which are shown
in FIG. 5 in the monitoring system 109 in addition to the other gas
sensors 65 and to the sensors 59, 67, 69, are connected
pneumatically or fluidically to another pump PA 56. Identical
elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5 are designated by the same
reference numbers in FIGS. 1a, 1b, 1c, 2, 3, 4, 5. This additional
pump PA 56 makes possible the feed of gas from an environment 5 via
an additional gas port 53, for example, of outside air from the
outside of the airplane or aircraft or of inside air from the cabin
or cockpit of the airplane or aircraft. The additional pump PA 56
is controlled by the control unit 70. Outside air from the outside
of the airplane or aircraft or inside air from the cabin or cockpit
of the airplane or aircraft can thus be fed via the additional gas
port 53. A simultaneous monitoring of gas concentrations in the
breathing mask 20 and of gas concentrations in the cockpit, cabin
or outside air is thus made possible. Additional sensors in the
sensor mechanism 60 may be configured to detect the current
situation of the airplane or aircraft by measurement. A current
flight situation with flight altitude, flight direction, flight
velocity, flight acceleration, flight position with orientation in
space (XYZ orientation) and flight situation or flight maneuver
(e.g., ascent, descent, curve flight, landing approach, start) can
be determined by the control unit (70) by means of the data of an
acceleration sensor 61, preferably configured as a 3-axis
acceleration sensor (3-axis accelerometer) in combination with an
altitude sensor 58 (altimeter), gyro sensor 63 and by the optional
addition of information of a compass sensor 62.
[0155] FIG. 6 shows a variant as a variant of FIG. 3, wherein the
pump PM 50 or the gas transport module is arranged at a gas outlet
49 of the monitoring system 100'. Compared to the variant shown in
FIG. 3 with the pump at the gas inlet of the monitoring system,
this has the advantage that no traces or impurities can reach the
monitoring system 100', especially the sensor mechanism 60 with a
carbon dixoide sensor 64 and with an oxygen sensor 68, from the
pump PM 50. Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6
are designated by the same reference numbers in FIGS. 1a, 1b, 1c,
2, 3, 4, 5, 6. Components that may be needed for controlling the
pump PM 50 and for the feed of quantities of gases are preferably
arranged in the immediate vicinity of the pump PM 50. A pressure
sensor 47, a flow sensor 48 and a shut-off valve 57 are arranged
for this purpose close to the pump PM 50. The flow sensor 48 is
used for a measurement-based control of the flow rate delivered by
the pump (PM) 50. After flowing through the pump PM 50 and the flow
sensor 48, the quantity of gas being delivered flows to the outside
of the monitoring system 100' into the environment 5. The pressure
sensor 47 is arranged upstream in the gas stream in relation to the
shut-off valve 57 such that the pressure measurement can detect the
mask pressure in the breathing mask 20, which pressure is identical
now to the pressure level at the gas inlet 51 and to the pressure
level in the measured gas line 10 in the closed state of the
shut-off valve 57 in the now no-flow state. As an alternative, the
pressure sensor may also be arranged at the gas stream in the
vicinity of the gas inlet, at the measured gas line 10 or close to
the gas sensors 60, 64, 68. A reversing valve 55, which, described
in a comparable manner as it was described in connection with the
reversing valve 55 in FIG. 4, makes possible a switching of
quantities or partial quantities of gas samples between the gas
inlet 51 and an additional gas port 52, is provided at the gas
inlet 51. The reversing valve is preferably configured as a 3/2-way
valve. This arrangement makes it possible to deliver, on the one
hand, breathing gas from the breathing mask 20 to the sensor
mechanism 60 at the gas inlet 51 by means of the pump PM 50, but it
is, moreover, also possible to deliver quantities of gas or gas
mixture through the additional gas inlet 52 by means of the pump PM
50 from an environment 5 to the sensor mechanism 60 and to detect
it by measurement by means of the sensor mechanism 60. The
reversing valve 55 is controlled by the control unit 70. Outside
air can thus be fed from the outside of the airplane or aircraft or
inside air can be fed from the cabin or cockpit of the aircraft via
the additional gas port 52 and--with control by the control unit
70--a monitoring of gas concentrations in the breathing mask 20,
cockpit, cabin or outside air can alternatingly be made possible.
To protect the sensor mechanism 60 from moisture or condensation,
which is fed from the breathing mask 20 through the measured gas
line 10 by means of the pump PM 50 to the sensor mechanism 60, a
filter element (HME filter) 54 may be arranged in a series
connection in the measured gas line or at the outlet of the
reversing valve 55.
[0156] Instead of the input element 80 configured in the form of a
switching element, as in the device 100 according to FIG. 3, an
acceleration sensor 61, which is configured and intended as an
alternative actuating or input element for detecting actuations
performed by the aviator by hand, is provided as an input element
in this embodiment 100' according to FIG. 6. By means of this
alternative actuating or input element or the acceleration sensor
61, the aviator, pilot or copilot is enabled to mark defined events
or situations of the flying operation and also to mark defined
personal events, situations or symptoms, for example, those related
to health, such as fever, racing heart or a feeling of dizziness in
the time course of the mission. This marking may be used by the
control unit 70 to combine the events or situations with time
information and then to store the combination of time information
and event or situation in a memory 75. The memory 75 may be
configured as a volatile or non-volatile memory (RAM, ROM, EEPROM)
and be arranged either as a fixed component or as a removable
memory module (USB stick, SD card) in or at the monitoring system
100'. Provision and/or exchange of the data with an external
analysis unit, not shown in the figures, may also be made possible,
for example, by means of a data interface 90 in a configuration
similar to that shown and described in FIG. 2b. This alternative
actuating or input element or the acceleration sensor 61 may thus
be used to complement the detected measured values of the sensor
mechanism 60 and the events and situations of the flying operation
by additional information, which is provided by means of the
alternative actuating or input element or of the acceleration
sensor 61 by the aviator, pilot or copilot, and to provide it with
time information, for example, in the form of a time stamp. It is,
however, also possible to configure the alternative actuating or
input element or the acceleration sensor 51 as a panic button,
which makes it directly possible for the aviator, pilot or copilot
to make themself noticeable in a situation that is a special
situation according to his perception, for example, a situation
with a special, objectively or subjectively perceived danger
situation or a risk situation. The marked measured values and/or
events, situations as well as the special situations may be made
available to the direct external environment, for example, by means
of the data interface 90 and may optionally be transmitted,
likewise directly (on-line) via a communication system of the
airplane or aircraft, to a ground station or to other airplanes or
aircraft. Furthermore, an analysis of the marked measured values
and/or events, situations and special situations later after the
mission (off-line) is made possible by means of the memory 75 or of
the data interface 90.
[0157] FIG. 7 shows, in a detail view as a detail drawing of the
area around the gas inlet 51 and unlike the view in FIG. 6, a
monitoring system 111 with an arrangement of filter element (HME
filter) 54, pump PM 50, sensor mechanism 60, pressure sensor 47,
flow sensor 48, shut-off valve 57 in an arrangement at the gas
inlet 51 without reversing valve for switching between a monitoring
of breathing gases of the pilot and a monitoring of the cabin air.
Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7 are
designated by the same reference numbers in FIGS. 1a, 1b, 1c, 2, 3,
4, 5, 6, 7. The pressure sensor 47 is arranged upstream, in the gas
stream in relation to the shut-off valve 57 such that the flow
measurement can detect in the now no-flow state the mask pressure
in the breathing mask 20, which is now identical to the pressure
level at the gas inlet 51 and in the measured gas line 10. As an
alternative, the pressure sensor 47 may also be arranged at the gas
stream in the vicinity of the gas inlet 51, at the measured gas
line 10 or close to the sensor mechanism 60 with the gas
sensors.
[0158] FIG. 8 shows, as a detail view as a detail drawing of the
area around the gas inlet 51 and unlike the view in FIGS. 6 and 7,
a monitoring system 111, 112 with an arrangement of filter element
(HME filter) 54, pump PM 50, sensor mechanism 60, pressure sensor
47 at the gas inlet 51 and with a reversing valve 55 configured as
a 3/2-way valve. Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4,
5, 6, 7, 8 are designated by the same reference numbers in FIGS.
1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8. The reversing valve 55 can release
the path for quantities of gas from an environment 5, e.g., the
cabin, to the sensor mechanism 60 and thus make a cabin air
monitoring possible. The reversing valve closes at the same time
the path for quantities of gas from the breathing mask 20. The
reversing valve 55 also has in this configuration according to FIG.
8 a manner of functioning as a shut-off valve for the performance
of a measurement maneuver for determining the pressure in the
breathing mask in addition to the switching between the measurement
of breathing gases and cabin air. The pressure sensor 47 is
arranged at the gas inlet 51 in relation to the reversing valve 55
and the measured gas line 10 such that in the state of the
reversing valve 55 with cabin air monitoring, the pressure
measurement can detect the mask pressure in the breathing mask 20,
which is now identical to the pressure level at the gas inlet 51
and in the measured gas line 10. The reversing valve 55 makes it
possible to switch between monitoring of breathing gases of the
pilot and monitoring of the cabin air.
[0159] FIG. 9 schematically shows a procedure 200 of a measurement
maneuver for determining a pressure level in the breathing mask 20
(FIG. 6) with a monitoring system 100' according to FIG. 6.
Identical elements in FIGS. 1a, 1b, 1c, 2, 3, 4, 5, 6, 7, 8, 9 are
designated by the same reference numbers in FIGS. 1a, 1b, 1c, 2, 3,
4, 5, 6, 7, 8, 9. Beginning with a start 201, the measurement
maneuver is carried out in an embodiment with a shut-off valve
(flow-lock valve) 57 (FIG. 6) by the control unit 70 (FIG. 6). A
deactivation 202 of the pump PM 50 (FIG. 6) is carried out after
the START 201, and the shut-off valve 57 (FIG. 6) is closed at that
time or with a slight time delay. The flow is thus stopped in the
measured gas line 10 (FIG. 6) and the sensor mechanism 60 (FIG. 6)
comes into a resting state. A first measurement operation of a
pressure measurement 204 is carried out to determine the static
pressure level. The shut-off valve 57 (FIG. 6) is then opened 205
and the pump PM 50 (FIG. 6) is activated 206. The pump PM 50 (FIG.
6) begins to suck quantities of gas from the breathing mask 20
(FIG. 6) through the measured gas line 10 (FIG. 6) and the sensor
mechanism 60 (FIG. 6) at a defined flow rate in the range of 50
mL/min to 100 mL/min A flow measurement 207 is carried out now with
the flow sensor 48 (FIG. 6) to control and monitor the flow rate.
An additional measurement operation of a pressure measurement 208
is subsequently carried out to determine the dynamic pressure
level. A difference value, which indicates the current pressure
drop over the pneumatic system, is determined 209 from the pressure
measured values of the first pressure measurement 204 and the
additional pressure measurement 208. The measurement maneuver
procedure thus comes to an end 210. The difference value thus
determined can then be made available and used to determine the
mask pressure during the further operation of the monitoring system
during the mission of the aircraft.
[0160] While specific embodiments of the invention have been shown
and described in detail to illustrate the application of the
principles of the invention, it will be understood that the
invention may be embodied otherwise without departing from such
principles.
LIST OF REFERENCE NUMBERS
[0161] 5 Environment, atmosphere, outside air, cockpit or cabin
[0162] 10 Measured gas line [0163] 20 Breathing mask [0164] 21 Gas
port at the breathing mask [0165] 24, 25 Hose lines [0166] 23, 23'
Connection element [0167] 29 Exhalation valve [0168] 40 Operating
elements [0169] 44, 45 Display elements [0170] 46 Wireless
interface, radio interface [0171] 47 Pressure sensor [0172] 48 Flow
sensor (flow sensor, delta P sensor) [0173] 49 Gas outlet [0174] 50
Gas delivery module, pump PM [0175] 51 Gas inlet [0176] 52, 53
Additional gas port [0177] 54 Filter element (HME filter) [0178] 55
Reversing valve (3/2-way valve), valve module [0179] 56 Additional
pump PA [0180] 57 Shut-off valve (flow lock valve) [0181] 58
Altitude sensor (altimeter) [0182] 59, 59'Humidity sensor [0183] 60
Sensor mechanism [0184] 61 Acceleration sensor [0185] 62 Compass
sensor [0186] 63 Gyro sensor [0187] 64, 64'Carbon dioxide sensor
[0188] 65 Additional gas sensor [0189] 66 Sensor [0190] 67,
67'Pressure sensor [0191] 68, 68'Oxygen sensor [0192] 69,69
Temperature sensor [0193] 70 Control unit [0194] 80 Input element
[0195] 90 Data interface [0196] 99 Person, pilot, aviator [0197]
100, 100'Monitoring system [0198] 108,109,110,111,112 Monitoring
system [0199] 200 Measurement maneuver procedure [0200] 201
Beginning, START [0201] 202 Pump: Deactivation [0202] 203 Shut-off
valve: Close valve [0203] 204 First pressure measurement: Static
pressure level [0204] 205 Shut-off valve: Open valve [0205] 206
Pump: Activation [0206] 207 Flow measurement [0207] 208 Additional
pressure measurement: Dynamic pressure level [0208] 209
Determination of the value of the current pressure drop [0209] 210
End, STOP
* * * * *